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  • Inorganic Chemistry  (658)
  • Aircraft Stability and Control  (57)
  • 1955-1959  (715)
  • 1950-1954
  • 1959  (715)
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Keywords
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Years
  • 1955-1959  (715)
  • 1950-1954
Year
  • 1
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    Some Research on the Lift and Stability of Wing-Body Combinations (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L55G06A
    Format: application/pdf
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  • 2
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    Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tall locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data by empirical correlation or theoretical means in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 10(exp 6) and at Mach numbers less than 0.25.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-49
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  • 3
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    A Flight Investigation of the Low-Speed Handling Qualities of a Tailless Delta-Wing Fighter Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Carrier landing-approach studies of a tailless delta-wing fighter airplane disclosed that approach speeds were limited by ability to control altitude and lateral-directional characteristics. More detailed flight studies of the handling-qualities characteristics of the airplane in the carrier-approach configuration documented a number of factors that contributed to the adverse comments on the lateral-directional characteristics. These were: (1) the tendency of the airplane to roll around the highly inclined longitudinal axis, so that significant sideslip angles developed in the roll as a result only of kinematic effects; (2) reduction of the rolling response to the ailerons because of the large dihedral effect in conjunction with the kinematically developed sideslip angles; and (3) the onset of rudder lock at moderate angles of sideslip at the lowest speeds with wing tanks installed. The first two of the factors listed are inseparably identified with this type of configuration which is being considered for many of the newer designs and may, therefore, represent a problem which will be encountered frequently in the future. The results are of added significance in the demonstration of a typical situation in which extraneous factors occupy so much of the pilot's attention that his capability of coping with the problems of precise flight-path control is reduced, and he accordingly demands a greater speed margin above the stall to allow for airspeed fluctuations.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-15-59A
    Format: application/pdf
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  • 4
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    A Buffet Investigation at High Subsonic Speeds of Wing-Fuselage-Tail Combinations having Sweptback Wings with NACA Four-Digit Thickness Distributions, Fences, and Body Contouring (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been made to determine the effect of wing fences, fuselage contouring, varying wing sweepback angle from 40 deg. to 45 deg., mounting the horizontal tail on an outboard boom) and wing thickness distribution upon the buffeting response of typical airplane configurations employing sweptback wings of high aspect ratio. The tests were conducted through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. For the combinations with 40 deg. of sweepback, the addition of multiple wing fences usually decreased the buffeting at moderate and high lift coefficients and reduced the erratic variation of buffet intensities with increasing lift coefficient and Mach number. Fuselage contouring also reduced buffeting but was not as effective as the wing fences. At most Mach numbers, buffeting occurred at higher lift coefficients for the combination with the NACA 64A thickness distributions than for the combination with the NACA four-digit thickness distributions. At high subsonic speeds, heavy buffeting was usually indicated at lift coefficients which were lower than the lift coefficients for static-longitudinal instability. The addition of wing fences improved the pitching-moment characteristics but had little effect on the onset of buffeting. For most test conditions and model configurations, the root-mean- square and the maximum values measured for relative buffeting indicated similar effects and trends; however, the maximum buffeting loads were usually two to three times the root-mean-square intensities.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-23-59A
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  • 5
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    Force-Test Investigation of the Stability and Control Characteristics of a 1/4-Scale Model of a Tilt-Wing Vertical-Take-Off-and-Landing Aircraft (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A wind-tunnel investigation has been made to determine the aerodynamic characteristics of a 1/4-scale model of a tilt-wing vertical-take-off-and-landing aircraft. The model had two 3-blade single-rotation propellers with hinged (flapping) blades mounted on the wing, which could be tilted from an incidence of 4 deg for forward flight to 86 deg for hovering flight. The investigation included measurements of both the longitudinal and lateral stability and control characteristics in both the normal forward flight and the transition ranges. Tests in the forward-flight condition were made for several values of thrust coefficient, and tests in the transition condition were made at several values of wing incidence with the power varied to cover a range of flight conditions from forward-acceleration (or climb) conditions to deceleration (or descent) conditions The control effectiveness of the all-movable horizontal tail, the ailerons and the differential propeller pitch control was also determined. The data are presented without analysis.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-11-3-58L
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  • 6
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    The Static and Dynamic Rotary Stability Derivatives at Subsonic Speeds of an Airplane Model Having Wing and Tail Surfaces Swept Back 45 degrees (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Wind-tunnel measurements were made of the static and dynamic rotary stability derivatives of an airplane model having sweptback wing and tail surfaces. The Mach number range of the tests was from 0.23 to 0.94. The components of the model were tested in various combinations so that the separate contribution to the stability derivatives of the component parts and the interference effects could be determined. Estimates of the dynamic rotary derivatives based on some of the simpler existing procedures which utilize static force data were found to be in reasonable agreement with the experimental results at low angles of attack. The results of the static and dynamic measurements were used to compute the short-period oscillatory characteristics of an airplane geometrically similar to the test model. The results of these calculations are compared with military flying qualities requirements.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-16-59A
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  • 7
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    Transonic Flutter Characteristics of a 45 deg Sweptback Wing with Various Distributions of Ballast Along the Leading Edge (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the use of ballast at the leading edge of a sweptback wing as a flutter fix has been made. The investigation was conducted in the Langley transonic blowdown tunnel with wing models which had an aspect ratio of 4, sweepback of the quarter-chord line of 450, and a taper ratio of 0.2. Four ballast configurations, which included different amounts of ballast distributed at two different span-wise locations, were investigated. Full-span sting-mounted models were employed. Data were obtained over a Mach number range from 0.65 to 1.32. Comparison of the data for the ballasted wings with data for a similar wing without ballast shows that in the often critical Mach number range between 0.85 and 1.05, the dynamic pressure required for flutter is increased by as much as 100 percent due to the addition of about 6 percent of the wing mass as ballast at the leading edge of the outboard sections. Furthermore, there are indications that similar benefits of leading-edge ballast can be obtained at Mach numbers above M = 1.1. Changing the spanwise location of the ballast and increasing the amount of the ballast by a factor of about 2 had very little additional effect on the dynamic pressure required for flutter. The possibility, therefore, exists that the beneficial effects obtained may be accomplished by using less than the minimum of about 6 percent of the wing mass as ballast as investigated in this paper.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-135
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  • 8
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    Effect of Wing Thickness and Sweep on the Oscillating Hinge-Moment and Flutter Characteristics of a Flap-Type Control at Transonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Free-oscillation tests were made in the Langley high-speed 7- by 10-foot tunnel to determine the effects of wing thickness and wing sweep on the hinge-moment and flutter characteristics of a trailing-edge flap-type control. The untapered semispan wings had full-span aspect ratios of 5 and NACA 65A-series airfoil sections. Unswept wings having ratios of wing thickness to chord of 0.04, 0.06, 0.08, and 0.10 were investigated. The swept wings were 6 percent thick and had sweep angles of 30 deg and 45 deg. The full-span flap-type controls had a total chord of 50 percent of the wing chord and were hinged at the 0.765-wing-chord line. Tests were made at zero angle of attack over a Mach number range from 0.60 to 1.02, control oscillation amplitudes up to about 12 deg, and a range of control-reduced frequencies. Static hinge-moment data were also obtained. Results indicate that the control aerodynamic damping for the 4-percent-thick wing-control model was unstable in the Mach number range from 0.92 to 1.02 (maximum for these tests). Increasing the ratio of wing thickness to chord to 0.06, 0.08, and then to 0.10 had a stabilizing effect on the aerodynamic damping in this speed range so that the aerodynamic damping was stable for the 10-percent-thick model at all Mach numbers. The 6-percent-thick unswept-wing-control model generally had unstable aerodynamic damping in the Mach number range from 0.96 to 1.02. Increasing the wing sweep resulted in a general decrease in the stable aerodynamic damping at the lower Mach numbers and in the unstable aerodynamic damping at the higher Mach numbers. The one-degree-of-freedom control-surface flutter which occurred in the transonic Mach number range (0.92 to 1.02) for the 4-, 6-, and 8-percent-thick unswept-wing-control models could be eliminated by further increasing the ratio of thickness to chord to 0.10. Flutter could also be eliminated by increasing the wing sweep angle to either 30 deg or 45 deg. The magnitude of variation in spring moment derivative with Mach number at transonic speeds was decreased by either increasing the ratio of wing thickness to chord or increasing the wing sweep angle.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-123
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  • 9
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    A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a Model of a Fighter-Type Airplane which Embodies Partial Body Indentation (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation was conducted to obtain the aerodynamic characteristics of a model of a fighter-type airplane embodying partial body indentation. The wing had an aspect ratio of 4, taper ratio of 0.5, 35 deg sweepback of the 0.25-chord line, and a modified NACA 65A006 airfoil section at the root and a modified NACA 65A004 airfoil section at the tip. The fuselage has been indented in the region of the wing in order to obtain a favorable area distribution. The results reported herein consist of the performance and of the static longitudinal and lateral stability and control characteristics of the complete model. The Mach number range extended from 0.60 to 1.13, and the corresponding Reynolds number based on the wing mean aerodynamic chord varied from 1.77 x 10(exp 6) to 2.15 x 10(exp 6). The drag rise for both the cambered leading edge and symmetrical wing sections occurred at a Mach number of 0.95. Certain local modifications to the body which further improved the distribution of cross-sectional area gave additional reductions in drag at a Mach number of 1.00. The basic configuration indicated a mild pitch-up tendency at lift coefficients near 0.70 for the Mach number range from 0.80 to 0.90; however, the pitch-up instability may not be too objectionable on the basis of dynamic-stability considerations. The basic configuration indicated positive directional stability and positive effective dihedral through the angle-of-attack range and Mach number range with the exception of a region of negative effective dihedral at low lifts at Mach numbers of 1.00 and slightly above.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-13-58L , L-476
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  • 10
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    Analytical Investigation of a Flicker-Type Roll Control for a Mach Number 6 Missile with Aerodynamic Controls Over An Altitude Range of 82,000 to 282,000 feet (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An analytical investigation has been carried out to determine the responses of a flicker-type roll control incorporated in a missile which traverses a range of Mach number of 6.3 at an altitude of 82,000 feet to 5.26 at an altitude of 282,000 feet. The missile has 80 deg delta wings in a cruciform arrangement with aerodynamic controls attached to the fuselage near the wing trailing edge and indexed 450 to the wings. Most of the investigation was carried out on an analog computer. Results showed that roll stabilization that may be adequate for many cases can be obtained over the altitude range considered, providing that the rate factor can be changed with altitude. The response would be improved if the control deflection were made larger at the higher altitudes. lag times less than 0.04 second improve the response appreciably. Asymmetries that produce steady rolling moments can be very detrimental to the response in some cases. The wing damping made a negligible contribution to the response.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-23-59L , L-211
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  • 11
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    Ground Simulator Studies of a Nonlinear Linkage in a Power Control System (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation was made to determine the characteristics of a nonlinear linkage installed in a power control system incorporated in a ground simulator. The nonlinear linkage provided for increased control-stick motion for relatively small simulator response at control motions near neutral. The quality of the control system was rated on the ease and precision with which various tracking tasks were performed by the pilots who operated the simulator. The results obtained with the nonlinear linkage installed in the control system were compared with those obtained by using the normal linear control system. Several combinations of nonlinearity of the linkage were tested for various dynamic characteristics of the simulator. It was found that the pilots were able to track almost as well with the nonlinear linkage installed as with the normal system. All of the pilots were of the opinion, however, that the nonlinearity was an undesirable feature in the control system because of the apparent lack of simulator response through the neutral range of the linkage where relatively large stick deflections could be made with very little simulator motion. The results showed that increased lag between the target and chair position, higher stick-force levels, and uneven stick forces due to the dynamics of the linkage were general characteristics of all the nonlinear linkage conditions tested. It was also found that for cases of low simulator damping, rapid control motions caused considerably higher overshoots when the nonlinear linkage was installed than were obtained for the normal linear control system. These characteristics were considered to be sufficiently undesirable to out-weigh the advantages to be gained from the use of a nonlinear linkage in the control system of an airplane.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-15-59L , L-174
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  • 12
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    Estimation of Static Longitudinal Stability of Aircraft Configurations at High Mach Numbers and at Angles of Attack Between 0 deg and +/-180 deg (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The possibility of obtaining useful estimates of the static longitudinal stability of aircraft flying at high supersonic Mach numbers at angles of attack between 0 and +/-180 deg is explored. Existing theories, empirical formulas, and graphical procedures are employed to estimate the normal-force and pitching-moment characteristics of an example airplane configuration consisting of an ogive-cylinder body, trapezoidal wing, and cruciform trapezoidal tail. Existing wind-tunnel data for this configuration at a Mach number of 6.86 provide an evaluation of the estimates up to an angle of attack of 35 deg. Evaluation at higher angles of attack is afforded by data obtained from wind-tunnel tests made with the same configuration at angles of attack between 30 and 150 deg at five Mach numbers between 2.5 and 3.55. Over the ranges of Mach numbers and angles of attack investigated, predictions of normal force and center-of-pressure locations for the configuration considered agree well with those obtained experimentally, particularly at the higher Mach numbers.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-1-17-59A
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  • 13
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    Effects of Fuselage Nose Length and a Canopy on the Low-Speed Oscillatory Yawing Derivatives of a Swept-Wing Airplane Model with a Fuselage of Circular Cross Section (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A wind-tunnel investigation was made at low speed in the Langley stability tunnel in order to determine the effects of fuselage nose length and a canopy on the oscillatory yawing derivatives of a complete swept-wing model configuration. The changes in nose length caused the fuselage fineness ratio to vary from 6.67 to 9.18. Data were obtained at various frequencies and amplitudes for angles of attack from 0 deg. to about 32 deg. Static lateral and longitudinal stability data are also presented.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-1-15-59L
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  • 14
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    Static Longitudinal Stability and Control Characteristics of an Unswept Wing and Unswept Horizontal-Tail Configuration at Mach Numbers from 0.70 to 2.22 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Results of an investigation of the static longitudinal stability and control characteristics of an aspect-ratio-3.1, unswept wing configuration equipped with an aspect-ratio-4, unswept horizontal tail are presented without analysis for the Mach number range from 0.70 to 2.22. The hinge line of the all-movable horizontal tail was in the extended wing chord plane, 1.66 wing mean aerodynamic chords behind the reference center of moments. The ratio of the area of the exposed horizontal-tail panels to the total area of the wing was 13.3 percent and the ratio of the total areas was 19.9 percent. Data are presented at angles of attack ranging"from -6 deg to +18 deg for the horizontal tail set at angles ranging from +5 deg to -20 deg and for the tail removed.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-11-59A
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  • 15
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    Static Stability Characteristics of Three Thick Wing Models with Parabolic Plan Forms at a Mach Number of 3.11 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An experimental investigation has been made to determine the static stability characteristics of three thick wing models with parabolic plan forms at a Mach number of 3.11 for angles of attack from about -6 to 16 deg. The primary variable was aspect ratio, with the plan-form area and the ratio of base height to span kept the same for all three models. All models had stable, linear pitching-moment curves about the quarter chord of the wing mean aerodynamic chord. The model with the lowest aspect ratio attained a maximum untrimmed lift-drag ratio of about 5.0 at an angle of attack of about 8 deg. Increasing the aspect ratio (which was accompanied by an increase in base area because the ratio of the base height to span was kept constant) caused a decrease in maximum lift-drag ratio. All models were directionally stable for the range of angle of attack of the tests. Addition of a vertical tail to the models caused an increase in the directional stability over the angle-of-attack range. In general, the lateral aerodynamic characteristics of the models were not linear functions of angle of attack over any appreciable angle-of-attack range.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-141 , L-597
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  • 16
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    Static Stability Characteristics of a Series of Hypersonic Boost-Glide Configurations at Mach Numbers of 1.41 and 2.01 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation of the static stability characteristics of several hypersonic boost-glide configurations has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 (with Reynolds numbers per foot of 2.90 x 10(exp 6) and 2.41 x 10(exp 6) respectively). This series of configurations consisted of a cone, with and without cruciform fins, a trihedron, two low-aspect-ratio delta wings that differed primarily in cross-sectional shape, and two wing-body configurations. All configurations indicated reasonably linear pitching-, yawing-, and rolling-moment characteristics for angles of attack to at least 12 deg. The maximum lift-drag ratio for the zero-thrust condition (base drag included) was about 3 for the delta-wing configurations and about 4 for the wing-body configurations.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-167
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  • 17
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    Experimental Flutter Investigation of Some Simple Models of a Boost Glide Vehicle Wing at Mach Numbers of 3.0 and 7.3 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Results of tests at Mach numbers of 3.0 and 7.3 for possible wing flutter of a series of models of a boost-glide-vehicle wing are presented herein. All of the models were tested at conditions which exceeded the proposed nominal design requirements for the full-scale vehicle; namely, dynamic pressure of 1,000 pounds per square foot at the test Mach numbers. None of the models experienced flutter; therefore, large margins of safety from wing flutter are indicated. However, the effects of body freedoms on the flutter characteristics and local types of flutter were not investigated.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-37 , HQ-E-DAA-TN54209
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  • 18
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    Transonic Flutter Characteristics of an Aspect-Ratio-4, 45 deg. Sweptback, Taper-Ratio-0.2 Plan Form (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The results of several flutter investigations to determine the effects of plan-form variations on the flutter characteristics of thin cantilevered wings at transonic Mach numbers have been reported previously. In the present investigation the data are extended to include a wing having an aspect ratio of 4, 45 of sweepback, and a taper ratio of 0.2. The data were obtained in the Langley transonic blowdown tunnel over a Mach number range from 0.6 to 1.4. The experimental results indicate an abrupt and rather large increase in both a flutter-speed parameter and a flutter-frequency parameter as the Mach number is increased from 1.05 to 1.10. The foregoing is interpreted as indicating a marked change in the flutter mode. Calculated flutter speeds, based on incompressible-flow aerodynamic coefficients, were too high by 20 percent or more throughout the subsonic Mach number range of the investigation. Calculated flutter frequencies were about 7 percent too high at a Mach number of 0.65 and were about 20 percent too high at a Mach number of 0.9. No significant independent effects of thickness were indicated for the plan form investigated as the thickness was changed from 3 to 4 percent chord.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-136
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  • 19
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    Effect of Tail Dihedral on Lateral Control Effectiveness at High Subsonic Speeds of Differentially Deflected Horizontal-Tail Surfaces on a Configuration having a Thin Highly Tapered Wing (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of tail dihedral on lateral control effectiveness of a complete-model configuration having differentially deflected horizontal-tail surfaces. Limited tests were made to determine the lateral characteristics as well as the longitudinal characteristics in sideslip. The wing had an aspect ratio of 3, a taper ratio of 0.14, 28.80 deg sweep of the quarter-chord line with zero sweep at the 80-percent-chord line, and NACA 65A004 airfoil sections. The test Mach number range extended from 0.60 to 0.92. There are only small variations in the roll effectiveness parameter C(sub iota delta) with negative tail dihedral angle. The tail size used on the test model, however, is perhaps inadequate for providing the roll rates specified by current military requirements at subsonic speeds. The lateral aerodynamic characteristics were essentially constant throughout the range of sideslip angle from 12 deg to -12 deg. A general increase in yawing moment was noted with increased negative dihedral throughout the Mach number range.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-1-58L
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  • 20
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    Theoretical Analysis of the Longitudinal Behavior of an Automatically Controlled Supersonic Interceptor During the Attack Phase (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase against a nonmaneuvering target is presented. Control of the interceptor's flight path is obtained by use of a pitch rate command system. Topics lift, and pitching moment, effects of initial tracking errors, discussion of normal acceleration limited, limitations of control surface rate and deflection, and effects of neglecting forward velocity changes of interceptor during attack phase.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-19
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  • 21
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    Static Stability and Control Characteristics of a 0.5-Scale Model of the Hughes GAR-11 Missile at Mach Numbers from 1.60 to 2.30 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Normal forces, axial forces, pitching moments, and rolling moments on the model and hinge moments on each of the four control surfaces were measured. Control surfaces were deflected from -35 deg to 15 deg in various combinations to produce pitching, yawing, and rolling moments on the model over a range of angles of attack from -5 deg to 25 deg at roll angles from -135 deg to 45 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-6-59A , AF-AM-162 , A-213 , AF-AM-162
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  • 22
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    Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of a Triangular Wing Configuration Equipped with a Canard Control, a Trailing-Edge-Flap Control or a Cambered Forebody (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results of an investigation to determine the static longitudinal stability and control characteristics of an aspect-ratio-2 triangular wing and body configuration equipped with either a canard control, a trailing-edge-flap control, or a cambered forebody are presented without analysis for Mach numbers from 0.70 to 2.22. The canard surface had a triangular plan form and a ratio of exposed area to total wing area of 7.8 percent. The hinge line of the canard was in the extended wing chord plane, 0.83 wing mean aerodynamic chord ahead of the reference center of moments. The trailing-edge controls were constant-chord full-span flaps with exposed area equal to 10.7 percent of the total wing area. The cambered body was a modified Sears-Haack body with camber only ahead of the wing apex. Data are presented for various canard and flap deflections at angles of attack ranging from -6 deg to +18 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-21-59A
    Format: application/pdf
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  • 23
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    Effect of the Proximity of the Wing First-Bending Frequency and the Short-Period Frequency on the Airplane Dynamic-Response Factor (1959)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The results are presented in the form of preliminary design charts which give a comparison between the dynamic-response factors of the semi-rigid case and the airplane longitudinal short-period case and between the dynamic-response factors of the semi-rigid case and the steady-state value of the airplane longitudinal short-period response. These charts can be used to estimate the first-order effects of the addition of a wing-bending degree of freedom on the short-period dynamic-response factor and on the maximum dynamic-response factor when compared with the steady-state response of the system.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-12
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  • 24
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    An Experimental Investigation to Determine the Effect of Speed-Brake Position on the Longitudinal Stability and Trim of a Swept-Wing Fighter Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 to determine the effects of adding underfuselage speed brakes. The results of brief spoiler-aileron lateral control tests also are included. The tests show acceptable trim and drag increments when the speed brakes are installed at the 32-71-inch fuselage station.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-188 , L-381
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  • 25
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    Low-Speed Measurements of Static and Oscillatory Lateral Stability Derivatives of a 1/5 Scale Model of a Jet-Powered Vertical-Attitude VTOL Research Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Force tests of the static and dynamic lateral stability characteristics of a VTOL airplane having a triangular wing mounted high on the fuselage with a triangular vertical tail on top of the wing and no horizontal tail have been made in the Langley free-flight tunnel. The static lateral stability parameters and the rolling, yawing, and sideslipping dynamic stability derivatives are presented without analysis.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-143 , L-640
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  • 26
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    Flutter Tests of Some Simple Models at a Mach Number of 7.2 in Helium Flow (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results of hypersonic flutter tests on some simple models are presented. The models had rectangular plan forms of panel aspect ratio 1.0, no sweepback, and bending-to-torsion frequency ratios of about 1/3. Two airfoil sections were included in the tests; double wedges of 5-, 10-, and 15-percent thickness and flat plates with straight, parallel sides and beveled leading and trailing edges. The models were supported by a cantilevered shaft. The double-wedge wings were tested in helium at a Mach number of 7.2. An effect of airfoil thickness on flutter speed was found, thicker wings requiring more stiffness to avoid flutter. A few tests in air at a Mach number of 6.9 showed the same thickness effect and also indicated that tests in helium would predict conservative flutter boundaries in air. The data in air and helium seemed to be correlated by piston-theory calculations. Piston-theory calculations agreed well with experiment for the thinner models but began to deviate as the thickness parameter MT approached and exceeded 1.0. A few tests on flat-plate models with various elastic-axis locations were made. Piston-theory calculations would not satisfactorily predict the flutter of these models, probably because of their blunt leading edges.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-8-59L , L-199
    Format: text
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  • 27
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    Dynamic Longitudinal and Directional Stability Derivatives for a 45 deg. Sweptback-Wing Airplane Model at Transonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was made at transonic speeds to determine some of the dynamic stability derivatives of a 45 deg. sweptback-wing airplane model. The model was sting mounted and was rigidly forced to perform a single-degree-of-freedom angular oscillation in pitch or yaw of +/- 2 deg. The investigation was made for angles of attack alpha, from -4 deg. to 14 deg. throughout most of the transonic speed range for values of reduced-frequency parameter from 0.015 to 0.040 based on wing mean aerodynamic chord and from 0.04 to 0.14 based on wing span. The results show that reduced frequency had only a small effect on the damping-in-pitch derivative and the oscillatory longitudinal stability derivative for all Mach numbers M and angles of attack with the exception of the values of damping coefficient near M = 1.03 and alpha = 8 deg. to 14 deg. In this region, the damping coefficient changed rapidly with reduced frequency and negative values of damping coefficient were measured at low values of reduced frequency. This abrupt variation of pitch damping with reduced frequency was a characteristic of the complete model or wing-body-vertical-tail combination. The damping-in-pitch derivative varied considerably with alpha and M for the horizontal-tail-on and horizontal-tail-off configurations, and the damping was relatively high at angles of attack corresponding to the onset of pitch-up for both configurations. The damping-in-yaw derivative was generally independent of reduced frequency and M at alpha = -4 deg. to 4 deg. At alpha = 8 deg. to 14 deg., the damping derivative increased with an increase in reduced frequency and alpha for the configurations having the wing, whereas the damping derivative was either independent of or decreased with increase in reduced frequency for the configuration without the wing. The oscillatory directional stability derivative for all configurations generally decreased with an increase in the reduced-frequency parameter, and, in some instances, unstable values were measured for the model configuration with the horizontal tail removed.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-39
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  • 28
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    The Synthesis of Optimum Homing Missile Guidance Systems with Statistical Inputs (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An analytical approach is presented which is applicable to the optimization of homing navigation guidance systems which are forced to operate in the presence of radar noise. The two primary objectives are to establish theoretical minimum miss distance performance and a method of synthesizing the optimum control system. The factors considered are: (1) target evasive maneuver, (2) radar glint noise, (3) missile maneuverability, and (4) the inherent time-varying character of the kinematics. Two aspects of the problem are considered. In the first, consideration is given only to minimization of the miss distance. The solution given cannot be achieved in practice because the required accelerations are too large. In the second, results are extended to the practical case where the limited acceleration capabilities of the missile are considered by placing a realistic restriction on the mean-square acceleration so that system operation is confined to the linear range. Although the exact analytical solution of the latter problem does not appear feasible, approximate solutions utilizing time-varying control systems can be found. One of these solutions - a range multiplication type control system - is studied in detail. It is shown that the minimum obtainable miss distance with a realistic restriction on acceleration is close to the absolute minimum for unlimited missile maneuverability. Furthermore, it is shown that there is an equivalence in performance between the homing and beam-rider type guidance systems. Consideration is given to the effect of changes in target acceleration, noise magnitude, and missile acceleration on the minimum miss distance.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-13-59A
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  • 29
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    Free-Spinning Characteristics of a 1/30-Scale Model of the Grumman WF-2 Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/30-scale model of the Grumman WF-2 airplane. The effects of control settings and movements upon the erect-spin and recovery characteristics for the flight gross-weight loading with normal center-of-gravity and rearward center-of-gravity positions were determined. For the inverted-spin tests, the flight gross-weight loading with normal center-of-gravity position was used. Brief tests were also made with the radome removed to determine the effect of the radome on the spin and recovery characteristics of the airplane. The results of the tests of the model indicate that erect spins of the airplane in the flight gross-weight loading with the normal (26.3-percent mean aerodynamic chord) center-of-gravity position and with the most rearward (30-percent mean aerodynamic chord) center-of-gravity position possible will be satisfactorily terminated by full rudder reversal to against the spin accompanied by movement of the elevator to at least two-thirds down. With the radome removed, the spin will be steeper and considerably more oscillatory than with the radome on. Recoveries by the preceding technique will be satisfactory. Inverted spins of the airplane will be satisfactorily terminated by full rudder reversal followed by neutralization of the longitudinal and lateral controls.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-24-59L , L-326 , NASA-AD-3134
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  • 30
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    The Static Longitudinal Stability and Control Characteristics in the Presence of the Ground of a Model Having a Triangular Wing and Canard (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A wind-tunnel investigation was made of the low-speed characteristics of a canard configuration having triangular wing and canard surfaces with an aspect ratio of 2. The exposed area of the canard was 6.9 percent of the total wing area. The canard hinge line was located at 0.35 of its mean aerodynamic chord and was 0.5 wing mean aerodynamic chord lengths forward of the wing apex. The ground effects, which made the lift more positive and the -Pitching moment more negative at a given angle of attack, were unaffected by the canard. The stability of the model at a constant canard hinge-moment coefficient decreased to 0 near a lift coefficient of 1.0. In addition, the maximum lift coefficient at which the canard could provide balance was decreased by ground effects to less than 1.0 if the moment center was as far forward as 0.21 of the wing mean aerodynamic chord. The relative magnitude of interference effects between the canard and the wing and body is presented.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-4-59A
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  • 31
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    Effect of Artificial Pitch Damping on the Longitudinal and Rolling Stability of Aircraft with Negative Static Margins (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A preliminary theoretical investigation has been made of the short-period longitudinal and steady-rolling (inertia coupling) stability of a hypersonic glider configuration for center-of-gravity locations rear-ward of the airplane neutral point. Such center-of-gravity positions for subsonic flight would improve performance by reducing supersonic and hypersonic static margins and trim drag. Results are presented of stability calculations and a simulator study for a velocity of 700 ft/sec and an altitude of 401,000 feet. With no augmentation, the airplane was rapidly divergent and was considered unsatisfactory in the simulator study. When a pitch damper was employed as a stability augmenter, the short-period mode became overdamped, and the airplane was easily controlled on the simulator. A steady-rolling analysis showed that the airplane can be made free of rolling divergence for all roll rates with an appropriate damper gain.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-5-59L
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  • 32
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    Investigation of the Stability of Very Flat Spins and Analysis of Effects of Applying various Moments Utilizing the Three Moment Equations of Motion (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Based on linearized equations of motion utilizing only the three moment equations and assuming only flat-spin conditions, it appears that contemporary designs (with the moment of inertia about the wing axis I(sub Y) considerably greater than the moment of inertia about the fuselage axis I(sub X) having positive values of C(sub l, sub p) (rolling-moment coefficient due to rolling) or positive values of C(sub l, sub beta) (rolling-moment coefficient due to sideslip) will probably not have a stable spin in the flat-spin region near an angle of attack of 90 deg. If the damping in pitch in flat-spin attitudes is zero, stable flat-spin conditions may not be possible on an airplane having the mass primarily distributed along the wings. The effect of moving ailerons with the spin or the effect of applying a positive pitching moment producing recovery for contemporary fighter designs will be greatest for large negative values of C(sub n, sub beta) (yawing-moment coefficient due to sideslip). In addition, for a certain critical value of positive C(sub n, sub beta), the rolling moment applied by moving ailerons with the spin or the application of a positive pitching moment will have no effect on reducing the spin rate.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-25-59L
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  • 33
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    Stability and Control Characteristics at Subsonic Speeds of a Flat-Top Arrowhead Wing-Body Combination (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A wind-tunnel investigation was made to determine the longitudinal- and lateral-stability derivatives of a flat-top wing-body configuration at Mach numbers from 0.22 to 0.90 and Reynolds numbers of 3.5 and 17 million. The wing had a leading-edge sweepback of 78.9 deg and a cathedral of 45 deg on the outer panels. The tests included the determination of the effectiveness of elevon and rudder controls and also an investigation of ground effects. The model was tested at angles of attack up to 28 deg and angles of sideslip up to 18 deg. The dynamic response of this configuration has been determined from the wind-tunnel data for a simulated airplane having a wing loading of 17.7 pounds per square foot. The longitudinal data show a forward shift in aerodynamic center of 10 percent of the mean aerodynamic chord as the lift coefficient is increased above 0.1. Although flown in the lift range of decreasing stability, the simulated airplane did not encounter pitch-up in maneuvers initiated from steady level flight with zero static margin unless a load factor of 2.2 was exceeded. This maneuver margin was provided by a large value of pitching moment due to pitching velocity. The number of cycles to damp the Dutch roll mode to half amplitude, the time constants of the roll subsidence and spiral divergence modes, and control effectiveness in roll are computed. The lateral stability is shown to be positive but is marginal in meeting the military specifications for today's aircraft. An analog computer study has been made in five degrees of freedom (constant velocity) which illustrates that the handling characteristics are satisfactory. Several programed rolling maneuvers and coordinated turns also illustrate the handling qualities of the airplane.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-5-59A
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  • 34
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    Stability Characteristics of Two Missiles of Fineness Ratios 12 and 18 with Six Rectangular Fins of Very Low Aspect Ratio Over a Mach Number Range of 1.4 to 3.2 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Two rocket-propelled missiles have been test flown by the Langley Pilotless Aircraft Research Division in order to study the stability characteristics of a body with six rectangular fins of very low aspect ratio. The fins, which had exposed aspect ratios of approximately o.o4 and 0.02 per fin, were mounted on bodies of fineness ratios of 12 and 18, respectively. Each body had a nose with a fineness ratio of 3.5 and a cylindrical afterbody. The body and the fin chord of the model having a fineness ratio of 12 were extended the length of 6 body diameters to produce the model with a fineness ratio of 18. The missiles were disturbed in flight by pulse rockets in order to obtain the stability data. The tests were performed over a Mach number range of 1.4 to 3.2 and a Reynolds number range of 2 x 10(exp 6) to 21 x l0(exp 6). The results of these tests indicate that these configurations with the long rectangular fins of very low aspect ratio showed little induced roll" with the missile of highest fineness ratio and longest fin chord exhibiting the least amount. Extending the body and fin chord of the shorter missile six body diameters and thereby increasing the fin area approximately 115 percent increased the lift-curve slope based on body cross-sectional area approximately 40 to 55 percent, increased the dynamic stability by a substantial amount, and increased the drag from 14 to 33 percent throughout the comparable Mach number range. The center-of-pressure location of both missiles remained constant over the Mach number range.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-2-58L
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  • 35
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    Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of the Static and Dynamic Stability Derivatives of an Airplane Model with an Unswept Wing and a High Horizontal Tail (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results are presented of a wind-tunnel investigation to evaluate the static and dynamic stability derivatives of a model with a low-aspect-ratio unswept wing and a high horizontal tail. In addition to results for the complete model, results were also obtained of the body alone, body and wing, and body and tail. Data were obtained in the Mach number range from 0.65 to 2.2, at a Reynolds number of 2 million based on the wing mean aerodynamic chord. The angle-of-attack range for most of the data was -11.5 deg to 18 deg. A limited amount of data was obtained with fixed transition. A correspondence between the damping in pitch and the static stability, previously noted in other investigations, was also observed in the present results. The effect observed was that a decrease (or increase) in the static stability was accompanied by an increase (or decrease) in the damping in pitch. A similar correspondence was observed between the damping in yaw and the static-directional stability. Results from similar tests of the same model configuration in two other facilities over different speed ranges are presented for comparison. It was found that most of the results from the three investigations correlated reasonably well. Estimates of the rotary derivatives were made using available procedures. Comparison with the experimental results indicates the need for development of more precise estimation procedures.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-5-59A
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  • 36
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    Low-Subsonic Measurements of the Static and Oscillatory Lateral Stability Derivatives of a Sweptback-Wing Airplane Configuration at Angles of Attack from -10 to 90 deg (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been conducted in the Langley free-flight tunnel at low-subsonic speeds to provide some basic information on the stability and control characteristics in the high angle-of-attack range of an airplane configuration typical of current design trends. The investigation consisted of static- and dynamic-force tests over an angle-of- attack range from -10 to 90 deg. The dynamic-force tests, which consisted of both linear- and rotary-oscillation tests, were conducted at values of the reduced-frequency parameter k of 0.10, 0.15, and 0.20. The configuration was directionally unstable for all angles of attack above about 15 deg but maintained positive effective dihedral, control effectiveness, and damping in roll and yaw over most of the angle-of-attack range tested. The effects of frequency on the oscillatory stability derivatives were found to be generally small, but in a few cases the effects were relatively large.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-20-59L , L-365
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  • 37
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    An Investigation of the Performance of Various Reaction Control Devices (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of a small-scale reaction control devices in still air with both subsonic and supersonic internal flows has shown that lateral forces approaching 70 percent of the resultant force of the undeflected jet can be obtained. These results were obtained with a tilted extension at a deflection of 40 deg. The tests of tilted extensions indicated an optimum length-to-diameter ratio of approximately 0.75 to 1.00, dependent upon the deflection angle. For the two geometric types of spoiler tabs tested, blockage-area ratio appears to be the only variable affecting the lateral force developed. Usable values of lateral force were developed by the full-eyelid type of device with reasonably small losses in the thrust and weight flow. Somewhat larger values of lateral force were developed by injecting a secondary flow normal to the primary jet, but for conditions of these tests the losses in thrust and weight flow were large. Relatively good agreement with other investigations was obtained for several of the devices. The agreement of the present results with those of an investigation made with larger-scale equipment indicates that Reynolds number may not be critical for these tests. In as much as the effects of external flow could influence the performance and other factors affecting the choice of a reaction control for a specific use, it would appear desirable to make further tests of the devices described in this report in the presence of external flow.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-11-59L , L-160
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  • 38
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    Flight Investigation of an Automatic Throttle Control in Landing Approaches (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A flight investigation of an automatic throttle control in landing approaches has been made. It was found that airspeed could be maintained satisfactorily by the automatic throttle control. Turbulent air caused undesirably large variations of engine power which were uncomfortable and disconcerting; nevertheless, the pilot felt that he could make approaches 5 knots slower with equal assurance when the automatic control was in operation.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-19-59L , L-432
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  • 39
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    Supersonic Jet Tests of Missile Stabilizers (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Seven stabilizers were tested at a Mach number of 2 in order to determine the effects of aerodynamic heating and loading on the structural stability of the stabilizer. The models differed in internal structure and postcure temperatures of the laminated Fiberglass skin. Tests were made at various stagnation temperatures between 440 F and 625 F. The postcure temperatures of the Fiberglass skins were found to affect significantly the ability of the model to withstand the imposed test conditions.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-121
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  • 40
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    Low-Speed Static Stability and Control Characteristics of a Model of a Right Triangular Pyramid Reentry Configuration (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the low-speed static stability and control characteristics of a model of a right triangular pyramid reentry configuration has been made in the Langley free-flight tunnel. The investigation showed that the model had generally satisfactory longitudinal and lateral static stability characteristics. The maximum lift-drag ratio was increased from about 3 to 5 by boattailing the base of the model.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-11-59L
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  • 41
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    Low-Subsonic Static Stability and Damping Derivatives at Angles of Attack From 0 deg to 90 deg for a Model with a Low-Aspect-Ratio Unswept Wing and Two Different Fuselage Forebodies (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been made in the Langley free-flight tunnel at low-subsonic speed to determine the static stability, control effectiveness, and damping in roll and yaw of a model with a low-aspect-ratio unswept wing and two different fuselage forebodies at angles of attack from 0 deg to 90 deg. Results were obtained with a fuselage configuration having a long pointed nose and a shorter rounded nose. Although the wing stalled at an angle of attack of about 12 deg, maximum lift did not occur until an angle of attack of about 40 deg or 50 deg was obtained. The static longitudinal stability of the model having a short rounded nose was greater than that of the model having a longer pointed nose over the entire angle-of-attack range. The pointed-nose model had large out-of-trim yawing moments above an angle of attack of about 40 deg. Shortening and rounding the nose of the model delayed these out-of-trim yawing moments to slightly higher angles of attack. Both models were directionally unstable above an angle of attack of about 20 deg, but both had positive effective dihedral over virtually the entire angle-of-attack range. At the higher angles of attack the pointed-nose model had generally better damping in roll than that of the rounded-nose model. Both models had very high damping in yaw at an angle of attack of about 50 deg or 60 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-1-22-59L
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  • 42
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    Some Effects of Yaw Damping on Airplane Motions and Vertical-Tail Loads in Turbulent Air (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results of analytical and flight studies are presented to indicate the effect of yaw damping on the airplane motions and the vertical-tail loads in rough air. The analytical studied indicate a rapid reduction in loads on the vertical tail as the damping is increased up to the point of damping the lateral motions to 1/2 amplitude in one cycle. Little reduction in load is obtained by increasing the lateral damping beyond that point. Flight measurements made in rough air at 5,000 and 35,000 feet on a large swept-wing bomber equipped with a yaw damper show that the yaw damper decreased the loads on the vertical tail by about 50 percent at 35,000 feet. The reduction in load at 5,000 feet was not nearly as great. Measurements of the pilot's ability to damp the lateral motions showed that the pilot could provide a significant amount of damping but that manual control was not as effective as a yaw damper in reducing the loads.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-17-59L , L-433
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  • 43
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    Pitch-Up Problem: A Criterion and Method of Evaluation (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A method has been described for predicting the probable relative severity of pitch-up of a new airplane design prior to initial flight tests. An illustrative example has been presented which demonstrated the use of this procedure for evaluating the pitch-up behavior of a large, relatively flexible airplane. It has also been shown that for airplanes for which a mild pitch-up tendency is predicted, the wing and tail loads likely to be encountered in pitch-up maneuvers would not assume critical values, even for pilots unfamiliar with pitch-up.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-7-59A
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  • 44
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    Sampled-Data Techniques Applied to a Digital Controller for an Altitude Autopilot (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Sampled-data theory, using the Z transformation, is applied to the design of a digital controller for an aircraft-altitude autopilot. Particular attention is focused on the sensitivity of the design to parameter variations and the abruptness of the response, that is, the normal acceleration required to carry out a transient maneuver. Consideration of these two characteristics of the system has shown that the finite settling time design method produces an unacceptable system, primarily because of the high sensitivity of the response to parameter variations, although abruptness can be controlled by increasing the sampling period. Also demonstrated is the importance of having well-damped poles or zeros if cancellation is attempted in the design methods. A different method of smoothing the response and obtaining a design which is not excessively sensitive is proposed, and examples are carried through to demonstrate the validity of the procedure. This method is based on design concepts of continuous systems, and it is shown that if no pole-zero cancellations are allowed in the design, one can obtain a response which is not too abrupt, is relatively insensitive to parameter variations, and is not sensitive to practical limits on control-surface rate. This particular design also has the simplest possible pulse transfer function for the digital controller. Simulation techniques and root loci are used for the verification of the design philosophy.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-14-59A , A-138
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  • 45
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    Preliminary Analysis of the Effect of Flow Separation Due to Rocket Jet Pluming on Aircraft Dynamic Stability During Atmospheric Exit (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A theoretical investigation was conducted to determine the effects of body boundary-layer separation resulting from a highly underexpanded jet on the dynamic stability of a typical rocket aircraft during an atmospheric exit trajectory. The particular flight condition studied on a digital computer for five degrees of freedom was at Mach 6.0 and 150,000 feet. In view of the unknown character of the separated flow field, two estimates of the pressures in the separated region were made to calculate the unbalanced forces and moments. These estimates, based on limited fundamental zero-angle-of-attack studies and observations, are believed to cover what may be the actual case. In addition to a fixed control case, two simulated pilot control inputs were studied: rate-limited and instantaneous responses. The resulting-motions with and without boundary-layer separation were compared for various initial conditions. The lower of the assumed misalinement forces and moments led to a situation whereby a slowly damped motion could be satisfactorily controlled with rate-limited control input. The higher assumption led to larger amplitude, divergent motions when the same control rates were used. These motions were damped only when the instantaneous control responses were assumed.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-22-59E , E-161
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  • 46
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    Exploratory Investigation at Mach Number of 2.01 of the Longitudinal Stability and Control Characteristics of a Winged Reentry Configuration (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation has been conducted to determine the longitudinal stability and control characteristics of a reentry configuration at a Mach number of 2.01. The configuration consisted of clipped delta wing with hinged wing-tip panels. The results indicate that deflecting the wing-tip panels from a position normal to the wing chord plane to a position coincident with the wing chord plane resulted in a stabilizing change in the pitching-moment characteristics but did not significantly affect the nonlinearity of the pitching-moment variation with angle of attack. The trailing-edge controls were effective in producing pitching moment throughout the angle-of-attack range for control deflections up to at least 600. The control deflection required for trim, however, varied nonlinearly with angle of attack. It would appear that this nonlinearity as well as the maximum deflection required for trim could be greatly decreased by utilizing a leading-edge control in conjunction with a trailing-edge control.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-178
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  • 47
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    A Flight Investigation to Determine the Lateral Oscillatory Damping Acceptable for an Airplane in the Landing Approach (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An F-86E airplane, in which servo actuation of the ailerons and rudder provides artificial variation of the important lateral and directional aerodynamic stability parameters, has been flown by test pilots of the NASA, U.S. Air Force, and one aircraft manufacturer to determine satisfactory and acceptable levels of lateral oscillatory damping in the landing approach. In addition to normal operational use, particular consideration was given to the emergency condition of failure of stability-augmentation equipment. In this study, the pilots' opinions of the airplane dynamic stability and control characteristics in smooth and simulated rough air have been recorded according to a numerical rating scale. The results are presented in the form of boundaries in terms of cycles to damp to half amplitude, 1/C(sub 1/2), or time to damp to half amplitude, 1/T(1/2) and bank-to-sideslip ratio, and are discussed in relation to existing flying-qualities criteria. Though the present results, which were obtained at 170 knots indicated airspeed and 10,000-feet altitude, indicated that increased damping is required with increased bank-to-sideslip ratio (as found in previous work), consideration of the dampers-failed condition indicated a great reduction in the minimum acceptable damping. At moderate values of bank-to-sideslip ratio, effects of lateral-oscillation period on pilot-opinion variation with damping appeared to be taken into account by use of the parameter 1/T(sub 1/2).
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-10-58A
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  • 48
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    A Wind-Tunnel Investigation of the Stall-Flutter Characteristics of a Supersonic-Type Propeller at Positive and Negative Thrust (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation has been made utilizing a three-blade, 10-foot- diameter, supersonic-ty-pe propeller to determine propeller flutter characteristics. The particular flutter characteristics of interest were (1) the effect of stall flutter on a propeller operating in positive and negative thrust, (2) the effect of stall flutter on a propeller operating with the thrust axis inclined, and (3) the variation of vibratory blade shear stresses as the stall flutter boundary is penetrated and exceeded. Thrust and power measurements were made for all test conditions. Wake and inflow surveys were made when appropriate, to define the thrust and torque distributions and the magnitude of the inflow velocity. Stress measurements were made simultaneously to obtain the propeller flutter and bending response. It was found when operating both in the positive and negative thrust regions that, for most cases after the onset of flutter, the magnitude of the flutter stresses at first increased rapidly with section blade angle P, after which further increases in 0 resulted in only a moderate increase or a reduction in stress. Thrust-axis inclination up to the limit of the tests (angle of attack of 15 deg and dynamic pressure of 40 psf) appeared to have no effect on stall flutter. The stall flutter stresses were found to be directly associated with the section thrust characteristics of the blades. The onset of flutter was found to occur simultaneously with the divergence of the section thrust variation with blade angle from linearity for stations outboard of the blade 0.8-radius station. The maximum flutter stresses appeared to be a function of the maximum section thrust obtained at or in the vicinity of the blade 0.8-radius station. In an attempt to correlate two-dimensional airfoil data with three-dimensional data to predict the stall angle of attack (divergence of the section thrust) of the blade sections, it was found that no consistent correlation could be obtained. Also, a knowledge of the inflow conditions appeared to be insufficient to account for differences in airfoil characteristics between the two-dimensional and the three-dimensional cases.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-9-59A
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  • 49
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    Effect of Horizontal-Tail Chord on the Calculated Subsonic Span Loads and Stability Derivatives of Isolated Unswept Tail Assemblies in Sideslip and Steady Roll (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Subsonic span loads and the resulting stability derivatives have been calculated using the discrete-horseshoe-vortex method for a systematic series of horizontal tails in combination with a vertical tail of aspect ratio 1.0 in order to provide information on the effect of varying the chord of the horizontal tail for isolated tail assemblies performing sideslip and steady-roll motions. In addition, the effects of horizontal-tail dihedral angle for the sideslip case were obtained. Each tail surface considered had a taper ratio of 0.5 and an unswept quarter-chord line. The investigation covered variations in horizontal-tail chord, horizontal-tail span, and vertical location of the horizontal tail. The span loads and the resulting total stability derivatives as well as the vertical- and horizontal-tail contributions to these tail-assembly derivatives are presented in the figures for the purpose of showing the influence of the geometric variables. The results of this investigation showed trends that were in agreement with the results of previous investigations for variations in horizontal-tail span and vertical location of the horizontal tail. Variations in horizontal-tail chord expressed herein in terms of the root-chord ratio, that is, the ratio of horizontal-tail root chord to vertical-tail root chord, were found to have a pronounced influence on most of the span loads and the resulting stability derivatives. For most of the cases considered, the rate of change of the span load coefficients and the stability derivatives with the root-chord ratio was found to be a maximum for small values of root-chord ratio and to decrease as root-chord ratio increased.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-1-59L , L-216
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  • 50
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    Effects of Large Wing-Tip Masses on Oscillatory Stability of Wing Bending Coupled with Airplane Pitch (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An examination of oscillatory stability for a straight-winged airplane with large concentrated wing-tip masses was made using wing-bending and airplane-pitching degrees of freedom and considering only quasi-steady aerodynamic forces. It was found that instability caused by coupling of airplane pitching and wing bending occurred for large ratios of effective wing-tip mass to total airplane mass and for coupled wing-bending frequencies near or below the uncoupled pitching frequency. Boundaries for this instability are given in terms of two quantities: (1) the ratio of effective tip mass to airplane mass, which can be estimated, and (2) the ratio of the coupled bending frequency to the uncoupled pitch frequency, which can be measured in flight. These boundaries are presented for various values of several airplane parameters.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-29-58A
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  • 51
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    An Experimental Investigation of the Effect of a Canard Control on the Lift, Drag, and Pitching Moment of an Aspect-Ratio 2.0 Triangular Wing Incorporating a Form of Conical Camber (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The results of an experimental investigation to determine the effect of a canard control on the lift, drag, and pitching-moment characteristics of an aspect-ratio-2.0 triangular wing incorporating a form of conical camber are presented. The canard had a triangular plan form of aspect ratio 2.0 and was mounted in the extended chord plane of the wing. The ratio of the area of the exposed canard panels to the total wing area was 6.9 percent, and the ratio of the total areas was 12.9 percent. Data were obtained at Mach numbers from 0.70 to 2.22 through an angle-of-attack range from -6 deg to +18 deg with the canard on, and with the canard off. To provide a basis for comparison, the canard was also tested with a symmetrical wing having the same plan form, aspect ratio, and thickness distribution as the cambered wing. The results of the investigation showed that at the high subsonic speeds the gain in maximum lift-drag ratio achieved by camber was considerably reduced by the addition of a canard. At the supersonic speeds, the addition of the canard did not change the effect of camber on the maximum lift-drag ratios.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-20-59A
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  • 52
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    Low-Speed Measurements of Oscillatory Lateral Stability Derivatives of a 1/7-Scale Model of the North American X-15 Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation to determine the low-speed rolling, yawing, and sideslipping derivatives of a 1/7-scale model which was used to represent the original configuration and a modified configuration of the North American X-15 airplane has been conducted in the Langley free-flight tunnel. The original model was modified to approximately represent the final airplane configuration by reducing the size of the fuselage side fairings and changing the vertical-tail arrangement. The effects of various tail arrangements were determined for both configurations and the effect of small forebody strakes was determined for the modified configuration only.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-144
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  • 53
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    Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0.30 to 2.85 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A cone with a blunt nose tip and a 10.7 deg cone half angle and an ogive with a blunt nose tip and a 20 deg flared cylinder afterbody have been tested in free flight over a Mach number range of 0.30 to 2.85 and a Reynolds number range of 1 x 10(exp 6) to 23 x 10(exp 6). Time histories, cross plots of force and moment coefficients, and plots of the longitudinal force,coefficient, rolling velocity, aerodynamic center, normal- force-curve slope, and dynamic stability are presented. With the center-of-gravity location at about 50 percent of the model length, the models were both statically and dynamically stable throughout the Mach number range. For the cone, the average aerodynamic center moved slightly forward with decreasing speeds and the normal-force-curve slope was fairly constant throughout the speed range. For the ogive, the average aerodynamic center remained practically constant and the normal-force-curve slope remained practically constant to a Mach number of approximately 1.6 where a rising trend is noted. Maximum drag coefficient for the cone, with reference to the base area, was approximately 0.6, and for the ogive, with reference to the area of the cylindrical portion, was approximately 2.1.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-199
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  • 54
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    Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A transonic flutter investigation has been made of models of the T-tail of the Blackburn NA-39 airplane. The models were dynamically and elastically scaled from measured airplane data in accordance with criteria which include a flutter safety margin. The investigation was made in the Langley transonic blowdown tunnel and covered a Mach number range from 0.73 to 1.09 at simulated altitudes extending to below sea level. The results of the investigation indicated that, if differences between the measured model and scaled airplane properties are disregarded, the airplane with the normal value of stabilizer pitching stiffness should have a stiffness margin of safety of at least 32 percent at all Mach numbers and altitudes within the flight boundary. However, the airplane with the emergency value of stabilizer pitching stiffness would not have the required margin of safety from symmetrical flutter at Mach numbers greater than about 0.85 at low altitudes. First-order corrections for some differences between the measured model and scaled airplane properties indicated that the airplane with the normal value of stabilizer pitching stiffness would still have an adequate margin of safety from flutter and that the flutter safety margin for the airplane with the emergency value of stabilizer pitching stiffness would be changed from inadequate to adequate. However, the validity of the corrections is questionable.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-SX-242 , L-648
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  • 55
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    Effects of Forebody Deflection on the Stability and Control Characteristics of a Canard Airplane Configuration with a High Trapezoidal Wing at a Mach Number of 2.01 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of forebody deflection on the stability and control characteristics of a canard airplane configuration. The configuration had a high trapezoidal aspect-ratio-3 wing, a trapezoidal canard surface, and a single swept vertical tail. Forebody deflection angles of 0 deg, 2 deg and deg were investigated. The results indicated that nose-up deflections of the forebody provided positive increments of pitching moment with little increase in drag and hence would be useful in reducing the pitch-control requirements and the attendant losses in lift-drag ratio due to trimming. Deflection of the forebody, however, aggravated the decrease in directional stability with increasing angle of attack by causing a loss in tail contribution and by increasing the instability of the wing-body combination.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-4-59L
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  • 56
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    Estimation of Directional Stability Derivatives at Moderate Angles and Supersonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A study of some of the important aerodynamic factors affecting the directional stability of supersonic airplanes is presented. The mutual interference fields between the body, the lifting surfaces, and the stabilizing surfaces are analyzed in detail. Evaluation of these interference fields on an approximate theoretical basis leads to a method for predicting directional stability of supersonic airplanes. Body shape, wing position and plan form, vertical tail position and plan form, and ventral fins are taken into account. Estimates of the effects of these factors are in fair agreement with experiment.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-1-58A
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  • 57
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    Flight Investigation of the Stability and Control Characteristics of a 1/4-Scale Model of a Tilt-Wing Vertical-Take-Off-and-Landing Aircraft (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a tilt-wing vertical-take-off-and-landing aircraft with the use of a remotely controlled 1/4-scale free-flight model. The model had two propellers with hinged (flapping) blades mounted on the wing which could be tilted up to an incidence angle of nearly 90 deg for vertical take-off and landing. The investigation consisted of hovering flights in still air, vertical take-offs and landings, and slow constant-altitude transitions from hovering to forward flight. The stability and control characteristics of the model were generally satisfactory except for the following characteristics. In hovering flight, the model had an unstable pitching oscillation of relatively long period which the pilots were able to control without artificial stabilization but which could not be considered entirely satisfactory. At very low speeds and angles of wing incidence on the order of 70 deg, the model experienced large nose-up pitching moments which severely limited the allowable center-of-gravity range.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-11-4-58L , L-120
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  • 58
    Electronic Resource
    Electronic Resource
    Schwefel - Stickstoff - Fluorverbindungen VI. Über Thioisodithiazylfluorid S3N2F2 (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 72-77 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: In addition to the formation of S4N4, greenish-yellow crystal sheets of S3N2F2 are deposited from a mixture containing SN2F2 and SNF at pressures form 600 to 700 mm Hg. S3N2F2 crystallizes in two polymorphic forms; the melting and decomposition points are 85 and 95 - 97° Cm, respectively; solubility in CCl4 at 20°C: 1.5 grs./100 grs. The observed formation of S3N2F2 is discussed in respect to the tendency of stable S—F-bond formation.
    Notes: Aus einem Gemisch von SN2F2 und SNF scheidet sich bei Drucken von 600 bis 700 Torr an der Wand des Reaktionskolbens ein gelber Beschlag ab, während gleichzeitig grüngelbe Kristallblättchen ins Innere des Kolbens wachsen. Bei letzteren handelt es sich um S3N2F2, das in zwei polymorphen Kristallarten auftritt. Fp. 85°C; Zers.-Pkt. 95-97°C. Löslichkeit in CCl4: 1,5 g/100 g bei 20°.Aus dem gelben Wandbeschlag wird durch Dekantieren mit Acetonitril S4N4 erhalten. Die Bildung von S3N2F2 wird diskutiert und festgestellt, daß die Tendenz zur Bildung stabiler S—F-Bindungen als Ursache für die Zersetzung von SN2F2 + SNF angesehen werden kann.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592980111
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  • 59
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    Infrarotspektroskopische und röntgenographische Untersuchungen am Quecksilber(II)-äthylendiaminchlorid (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 142-151 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The reaction between 1 mol mercuric chloride and 1 mol ethylenediamine (I) leads in aqueous and in diluted alcoholic solutions to a mixture of mercuric chloride and mercuric ethylenediamine chloride, Hg(NH2CH2CH2NH2)Cl2 (II). It is possible to get the compound (II) in pure state in absolute alcolholic solution. X-ray and infrared investigations give evidence for a chain-structure of (II) with (I) bounded in the trans-form.
    Notes: In wäßrigen und verdünnten alkoholischen Lösungen reagieren 1 Mol Quecksilber(II)-chlorid und 1 Mol Äthylendiamin unter Bildung unlöslicher Produkte, die aus Gemischen von Hg(NH2—CH2—CH2—NH2)Cl2 und HgCl2 bestehen. Wird die Reaktion unter Wasserausschluß in absolutem Alkohol ausgeführt, so entsteht reines Quecksilber(II)-äthylendiaminchlorid, Hg(en)Cl2 (en = Äthylendiamin). Durch die Diskussionen des Debyeogramms und des Infrarotspektrums der Verbindung können Ringstrukturen ausgeschlossen werden; es liegt eine Kettenstruktur mit trans-Stellung der XH2-Gruppen (X = N oder C) der Äthylendiamin-Molekel vor.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592980305
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  • 60
    Electronic Resource
    Electronic Resource
    Darstellung und thermische Zersetzung der Dichlorphosphorsäure H[PO2Cl2] (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 152-163 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Pure crystallizable dichlorophosphoric acid H[PO2Cl2] is prepared by reaction of dichlorophosphoric acid anhydride P2O3Cl4 with the calculated amount of water at temperatures below -30°C.When heated under reduced pressure (12 mm), and hydrogen chloride simultaneously is passed through, the dichlorophosphoric acid splits off water and is therefore again transformed into the dichlorophosphoric acid anhydride P2O3Cl4.Contrary to this the dichlorophosphoric acid decomposes, when heated under atmospheric pressure, mainly by splitting off HCl.
    Notes: Reine, kristallisierbare Dichlorphosphorsäure H[PO2Cl2] läßt sich durch Reaktion von Dichlorphosphorsäureanhydrid P2O3Cl4 mit der berechneten Menge Wasser bei Temperaturen unterhalb -30°C darstellen.Beim Erhitzen unter vermindertem Druck (12 mm) und gleichzeitigem Durchleiten von Chlorwasserstoff spaltet die Dichlorphosphorsäure Wasser ab und geht dadurch wieder in das Dichlorphosphorsäureanhydrid P2O3Cl4 über.Dagegen zersetzt sich die Dichlorphosphorsäure beim Erhitzen unter Atmosphärendruck vorwiegend unter HCl-Abspaltung.
    Additional Material: 1 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592980306
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  • 61
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    Über Phosphornitrilfluoride (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 193-193 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592980309
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  • 62
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    Über die Einwirkung der Halogenate auf Vanadin(III)-oxyd in wäßriger Lösung (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 194-201 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Vanadium(III)oxide, V2O3, is autocatalytically oxidized to vanadium(V)oxide or vanadates(V) by acid or neutral solutions of alkali metal chlorates, bromates, iodates, and periodates. By perchlorate ions, V2O3 is converted to vanadium(IV) compounds. The influence of pH and buffer systems has been investigated. The velocity of oxidation decreases from periodate, bromate, iodate, chlorate to perchlorate. In alkaline solutions the reaction of iodates is greater than that of bromates.
    Notes: Vanadin(III)-oxyd, V2O3, wird sowohl in saurer als auch ursprünglich neutraler Lösung der Alkalichlorate, -bromate, -jodate und -perjodate zu Vanadin(VI)-oxyd bzw. Vanadat und bei der Einwirkung von Perchlorationen langsam zur Vanadin(IV)-stufe oxydiert. Die Reaktionen verlaufen offenbar autokatalytisch. Die Halogenate wirken auch dann oxydierend, wenn der Einfluß der bei den Reaktionen gebildeten Wasserstoffionen durch Zusatz von Natriumhydrogencarbonat oder Calciumcarbonat zum Reaktionsgemisch aufgehoben wird und sogar unter alkalischen Bedingungen, wenn auch langsamer als in ungepufferten Lösung. Die Halogenate werden allgemein zur Halogenidstufe reduziert mit Ausnahme von Perjodat, das, falls reichlich von ihm vorhanden ist, zu Jodat reduziert wird. Die Oxydationsgeschwindigkeit nimmt in der Reihenfolge: Perjodat 〉 Bromat 〉 Jodat 〉 Chlorat 〉 Perchlorat ab. In alkalischen Lösungen oxydieren die Jodate schneller als die Bromate.
    Additional Material: 5 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592980310
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  • 63
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    Spektroskopische Untersuchungen an Siliciumverbindungen. VIII. Die Schwingungsspektren einiger Tetramethyldisiloxane (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 78-86 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The Raman and infrared spectra of compounds of the type X (CH3)2SiOSi(CH3)2X (X = H, OH, Cl, C6H5 are reported and the frequencies are assigned. The shift of the valence frequencies of the framework is briefly discussed. The approximate valence force constant of the SiOSi bond in HO(CH3)2SiOSi(CH3)2OH is calculated to 4,97 mdyn/Å.
    Notes: Die Raman- und IR-Spektren der Verbindungen X(CH3)2SiOSi(CH3)2X (X = H, OH, Cl und C6H5) werden mitgeteilt und die Frequenzen den einzelnen Schwingungsformen zugeordnet. Der Gang der Valenzfrequenzen des Gerüstes wird kurz diskutiert. Für das Tetramethyldioxydisiloxan wird die angenäherte Valenzkraftkonstante für die Siloxanbindung zu 4,97 mdyn/Å berechnet.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990110
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  • 64
    Electronic Resource
    Electronic Resource
    Masthead (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959) 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990301
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  • 65
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    Zur Frage des Reaktionsmechanismus des HCOOH-Zerfalls an Ni-Oberflächen. „Über den Mechanismus des Ameisensäuredampf-Zerfalls am Nickel“ (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 151-152 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: A mechanism of the decomposition of the formic acid on a surface of nickel is proposed.
    Notes: Es wird ein Mechanismus der genannten Reaktion angegeben.
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    URL: http://dx.doi.org/10.1002/zaac.19592990305
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    Spektroskopische Untersuchungen an Siliciumverbindungen. IX. Über die Bindungsverhältnisse in der Siliciumchemie (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 138-150 
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    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The bonds between silicium and elements of a great electronegativity are customary stronger than single bonds. This is shown by the valence force constants. The valence frequencies of substituted compounds indicate that strong electronegative substituends strengthen adjacent bonds. The mechanism of this strengthening is discussed.
    Notes: Die Valenzkraftkonstanten für Bindungen zwischen Silicium und stark elektronegativen Partnern zeigen, daß diese Bindungen in der Regel stärker als normale Einfachbindungen sind. Die Valenzfrequenzen in gemischt substituierten Verbindungen lassen erkennen, daß stark elektronegative Substituenten benachbarte Bindungen verstärken. Der Mechanismus dieser Bindungsverstärkungen wird diskutiert.
    Additional Material: 18 Tab.
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    Bleiverbindungen mit Apatitstruktur, insbesondere Blei-Jod- und Blei-Brom-Apatite (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 41-50 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The compounds Pb5(XO4)3Z (with X = P, As, V and Z = F, Cl, Br, J) have been prepared and investigated by X-ray analysis. With the exception of Pb5(PO4)3J, all compounds crystallize in apatite structure which is orthorhombically deformed in the case of Pb5(AsO4)3J.
    Notes: Es wird die Synthese von Bleiapatiten der Zusammensetzung Pb5(XO4)3Z [X = P, As, V und Z = F, Cl, Br, J] beschrieben. Röntgenaufnahmen ergeben in allen Fällen außer Pb5(PO4)3J die Apatitstruktur, im Falle des Pb5(AsO4)3J ist sie rhombisch deformiert. Einige Strukturdaten dieser Verbindungen werden mitgeteilt.
    Additional Material: 3 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000104
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    Zur Kenntnis der Chemie der Metallcarbonyle in flüssigem Ammoniak. IV. Über Neue Substitutionsprodukte des Cr(CO)6 mit aromatischen Aminen (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 51-60 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: By interaction of alkali pentacarbonyl chromates(-II) with aromatic mono-, di-, and triamines at room temperature only pentacarbonyl amine chromium(0) compounds are formed. Wheras m- and p-phenylene diamine are linked with two and 1, 3, 5-triaminobenzene with three Cr(CO)5-groups, o-phenylene diamine forms a corresponding compound with only one Cr(CO)5-group. Unlike ethylene diamine or cyclohexane diamine(1,2) o-phenylene diamine does not give a tetracarbonyl chromium(0) compound.
    Notes: Bei der Umsetzung von Alkali-pentacarbonyl-chromaten(-II) mit wäßrigen Lösungen von aromatischen Mono-, Di- und Triaminen bei gewöhnlicher Temperatur erhält man stets Pentacarbonyl-amin-chrom(0)-verbindungen, die sich als echte Substitutions-produkte des Cr(CO)6 erweisen. Während m- und p-Phenylendiamin zwei und 1,3,5-Triaminobenzol drei Cr(CO)5-Gruppen zu binden vermögen, erhält man im Falle des o-Phenylendiamins eine entsprechende Verbindung mit nur einer Cr(CO)5-Gruppe. Insbesondere entsteht bei letzterem - im Gegensatz zum Äthylendiamin - keine Tetracarbonyl-chrom(0)-verbindung. Eine solche bildet sich hingegen, wenn man an Stelle des o-Phenylendiamins das hydrierte o-Phenylendiamin, also Cyclohexandiamin(1,2), zur Reaktion bringt.
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    URL: http://dx.doi.org/10.1002/zaac.19593000105
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    Beiträge zur Chemie der Elemente Niob und Tantal. XXI. Präparative Untersuchungen mit niederen Niobchloriden (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 1-32 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The system niobium-chlorine has been investigated.The formation of niobiumtrichloride, with a composition range from NbCl2.67 to NbCl3.1, has been studied by thermal decomposition of niobium tetrachloride, reduction of NbCl5 with hydrogen, and the chemical transport reaction: \documentclass{article}\pagestyle{empty}\begin{document}$${\rm NbcL}_{\rm X} {\rm f + (4 - x)NbCl}_{\rm 5} {\rm g = (5 - x)NbCl}_{\rm 4} {\rm g}$$\end{document}.The thermal and chemical properties of the niobiumtrichloride phase are described.Niobium(II)-chloride which is a stoichiometric compound is formed in the reactions Nb+NbCla2.67, NbSNbCI5, and NbCl5+H. There is no evidence for the existence of niobium (I)-chloride.
    Notes: Das Niobtrichlorid besitzt einen großen Homogenitätsbereich. Die Phasengrenzen liegen bei den Zusammensetzungen NbCl3,1 und NbCl2,67. Diese Grenzzusammensetzungen fallen schon beim thermischen Abbau des Niobtetrachlorids und bei der Reduktion von NbCl5 mit H2 auf. Weiteren Aufschluß geben Experimente, bei denen die Trichloridphase NbClx durch eine chemische Transportreaktion \documentclass{article}\pagestyle{empty}\begin{document}$${\rm NbcL}_{\rm X} {\rm f + (4 - x)NbCl}_{\rm 5} {\rm g = (5 - x)NbCl}_{\rm 4} {\rm g}$$\end{document} als Gleichgewichtsbodenkörper gewonnen wird. Die Zusammensetzung der Trichloridphase hängt in der zu fordernden Weise vom NbCl5-Druck ab. Aus Pulverdiagrammen und aus der Farbe der Trichlorid-Präparate läßt sich ebenfalls die Breite der Trichloridphase und auch die Zusammensetzung eines im homogenen Gebiet liegenden Präparats ableiten.Angaben über das Niobtrichlorid hinsichtlich seines thermischen und chemischen Verhaltens werden zusammengestellt.Niob(II)-chlorid wird aus Nb + NbCl2,67 gewonnen. Auch beim Erhitzen von Nb im NbCl5-Argon-Strom und bei der Reduktion von NbCl5 mit H2 ist die NbCl2-Bildung nachweisbar. NbCl2 besitzt keine erhebliche Phasenbreite. Das chemische und thermische Verhalten des NbCl2 werden studiert.Das metallische Niob löst keine nachweisbaren Cl-Mengen. Ein Niob(I)-chlorid wurde nicht gefunden.Zusammenfassend werden die Phasenverhältnisse im System Niob-Chlor dargestellt und weitere Probleme der Trichloridphase erörtert.Das letzte Kapitel bringt Analysenverfahren.
    Additional Material: 16 Ill.
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    Herstellung und Eigenschaften der Ternären Nitride von Vanadin, Niob und Tantal der Zusammensetzung Li7MeN4 (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 61-71 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The compound Li7VN4 containing vanadium(V) has been prepared by heating Li3N and VN in nitrogen atmosphere to a temperature of 680 °C. Li7VN4 crystallizes in an superstructure of fluorite lattice (space group T4d with a = 9.604 Å).Similarly, the compounds Li7NbN4 and Li7 TaN4 have been synthesized.
    Notes: 1. Durch Erhitzen von Li3N und VN in einer Stickstoffatmosphäre auf 680 °C wurde die Verbindung Li7VN4 hergestellt. Die Oxydationsstufe 5 des Vanadins wurde mit drei verschiedenen Methoden bestimmt. Die ternäre Verbindung ist thermisch beständiger als die zwei binären Nitride. Li7VN4 kristallisiert in einer Überstruktur des Flußspatgitters in der Raumgruppe T4d mit a = 9,604 Å. Ein ternäres Nitrid niedrigerer Oxydationsstufe konnte nicht hergestellt werden.2. Entsprechende Versuche führten zu den Verbindungen Li7NbN4 und Li7TaN4; diese Verbindungen sind chemisch und thermisch etwas stabiler als die Vanadinverbindung.
    Additional Material: 3 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000106
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    Über Halogenide des dreiwertigen Titans (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 213-226 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: A technical alteration of the TiCl3-preparation according to SHERFEY is described.The phase diagrams of the systems NaCl/TiCl3, KCl/TiCl3 and KBr/TiBr3 were investigated by thermal analysis. There exist the compounds: Na3TiCl6 (incongruent m. p. = 553° C), K3TiCl6 (m. p. = 783° C), K2TiCl5 (incongruent m. p. = 605° C), K3TiBr6 (m. p. = 662° C). The results were confirmed by microscopic and X-rax methods.In the NaCl- and KCl-rich melts exists the complex [TiCl6]3- probably.
    Notes: Eine technische Abänderung der TiCl3-Darstellung nach SHERFEY wird mitgeteilt.Die Untersuchung der Systeme NaCl/TiCl3, KCl/TiCl3 und KBr/TiBr3 mit Hilfe der Differential-Thermoanalyse ergab folgendes: Im System NaCl/TiCl3 existiert die Verbindung Na3TiCl6. Sie schmilzt inkongruent bei 553° C. Das Zustandsdiagramm KCl/TiCl3 zeigt die Verbindungen K3TiCl6 (Schmp. = 783° C) und K2TiCl5 an, wobei die letztere bei 605° C inkongruent schmilzt. Im System KBr/TiBr3 tritt die bei 662° C kongruent schmelzende Verbindung K3TiBr6 auf.Das Ergebnis der thermischen Analyse wird durch mikroskopische und röntgenographische Untersuchungen gesichert.Die Berechnung der Liquiduskurve auf der NaCl- bzw. KCl-reichen Seite der Zustandsdiagramme legt nahe, die Existenz von [TiCl6]3--Ionen in der Schmelze anzunehmen.
    Additional Material: 7 Ill.
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    Masthead (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959) 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990501
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    Zur Kenntnis des Verhaltens von Nichtmetallchalkogeniden gegenüber flüssigem Ammoniak. III. Das Verhalten von Tetraphosphor-heptasulfid gegenüber flüssigem Ammoniak (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 241-251 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Tetraphosphorus-heptasulfide, P4S7, undergoes disproportionation in liquid ammonia at a temperature of -33° C according to the equation mentioned in „Inhaltsübersicht“.Tetraphosphorus-heptasulfide, P4S7, undergoes disproportionation in liquid ammonia at a temperature of -33° C according to the equation mentioned in „Inhalts-übersicht“.From the reaction products, the properties of which are described there is evidence for the structure of P4S7, determined by X-ray diffraction(4). The trimer orange-coloured [P3S3(NH)4]4-anion is supposed to have a cyclic structure.The thermal decomposition of (NH4)3[PS4] and (NH4)2[PS3NH2], yielding P4N5, is discussed.
    Notes: Während die beiden niederen Phosphorsulfide(2) P4S3 und P4S5 mit flüssigem Ammoniak bei -33° unter Bildung von Ammoniumverbindungen mit vier P-atomen in der Molekel reagieren und P4S10(3) einfach gebaute Thiophosphate bildet, unterliegt Tetraphosphor-heptasulfid in diesem Medium gemäß 2P4S7 + 17 NH3 → (NH4)3[PS4] + 2 (NH4)2[PS3NH2] + (NH4)3[P3S3(NH)3] + NH4[P2SN] der Disproportionierung.Der obige Reaktionsverlauf läßt sich einerseits durch quantitative Erfassung der sich in ihrer Löslichkeit unterscheidenden Thiophosphate (NH4)3[PS4] und (NH4)2[PS3NH2], andererseits durch Isolierung der Verbindung [P3S3(NH)3], in der der Phosphor die Oxydationszahl +III einnimmt, nachweisen. Die experimentellen Ergebnisse lassen sich aus der für das P4S7 röntgenographisch nachgewiesenen Struktur(4) ableiten.Die Eigenschaften der erhaltenen Verbindungen werden beschrieben und die Ergebnisse des thermischen Abbaus von (NH4)3[PS4] und (NH4)2[PS3NH2], der in beiden Fällen schließlich zu P3N5 führt, diskutiert.Dem trimeren orangefarbenen Thio-imidophosphit-anion [P3S3(NH)3]3- wird ringförmige Struktur zugeschrieben.
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    Magnetochemische Untersuchungen im System FeO1 + x · MgO (O 〈x〈 0,5) (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 271-280 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The magnetic susceptibility of FeO1+x · 0,925 MgO (0 〈 x 〈 0,5) at 700, 750, 800, 850 and 900° C has been measured. The results are compared with values calculated under certain conditions and with the magnetic susceptibility of the system Fe—O, received in previous investigations.The isotherms of the susceptibility of magnesiowüstite (FeO1+y · 0,925 MgO) and wüstite (FeO1+y) allow to make some conclusions of the structure of the magnesiowüstite phase. It seems very probable that the ions Fe3+ both in magnesiowüstite and in wüstite occur in the form of accumulations. This „submicroheterogenity“ does not mean that magnesiowüstite from the point of view of thermodynamics consists of two solid phases.The homogeneity range of magnesiowüstite phase spreads at 700° C from FeO1,04 · 0,925 MgO to FeO1,09 · 0,925 MgO and at 900° C about FeO1,015 · 0,925 MgO to about FeO1,11 · 0,925 MgO.
    Notes: Im System FeO1+x · 0,925 MgO (0 〈 x 〈 0,5) wurde für 15 Präparate die magnetische Suszeptibilität bei 700°, 750°, 800°, 850° und 900°C gemessen. Die Ergebnisse werden mit den unter bestimmten Voraussetzungen berechneten Suszeptibilitäten und mit den für das System Fe—O früher erhaltenen experimentellen Werten verglichen. Aus dem Verlauf der Suszeptibilitätsisothermen in den Homogenitätsbereichen der „Magnesiowüstit“-Phase (feste Lösungen von FeO1+y und 0,925 MgO) und der Wüstitphase (FeO1+y) konnten gewisse Schlüsse in bezug auf die Struktur der „Magnesiowüstit“-Phase gezogen werden. Es ist wahrscheinlich, daß die Fe3+-Ionen im Magnesiowüstit, ähnlich wie im Wüstit, in Form von Ansammlungen vorhanden sind. Diese „Submikroinhomogenität“ bedeutet nicht, daß Magnesiowüstit im thermodynamischen Sinne aus zwei festen Phasen besteht.Der Homogenitätsbereich der Magnesiowüstitphase erstreckt sich bei 700° C von FeO1,04 · 0,925 MgO bis FeO1,09 ·0,925 MgO und bei 900° C von FeO1,015 · 0,925 MgO bis ungefähr FeO1,11 · 0,925 MgO.Das Curie-Weiss-Gesetz wird von den im Homogenitätsbereich der Magnesiowüstitphase liegenden Präparaten befolgt.Die Abhängigkeit der magnetischen Suszeptibilität von der Zusammensetzung bei höheren Sauerstoffgehalten (x 〉 1,1) ist infolge des Auftretens zweier fester Phasen veränderlicher Zusammensetzung kompliziert.
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    Schwermetallkomplexe mit Thiopicolinsäure-anilidBald nach dem Einreichen des Manuskriptes der vorliegenden Arbeit erschien über den gleichen Gegenstand eine Veröffentlichung von F. Lions u. K. F. Martin, J. Amer. chem. Soc. 80, 1591 (1958). Auf die Ergebnisse der australischen Autoren wollen wir in unserer zweiten diesbezüglichen Publikation eingehen. (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 281-291 
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    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Thiopicolinic acid anilide reacts with ions of heavy metals to form inner complex salts. Complexes of 12 metals have been prepared. The coordination compound with Fe(II)-ions is deep violet.
    Notes: Thiopicolinsäure-anilid fungiert gegenüber Schwermetallionen, besonders azo- und chalkophilen, als Innerkomplexligand wie als Neutralligand(1). Das Anilid wird als Anion der tautomeren Iminothiol-Form von dem betreffenden Metallion innerkomplex koordiniert, wobei je nach Ladungs- und charakteristischer Koordinationszahl des Zentrums entweder ladungslose oder Acido-Innerkomplexe entstehen. Analytisch definierte Komplexe wurden von 12 verschiedenen Metallen gewonnen, wobei die sehr intensive Violettfarbe der Eisen(II)-komplexe hervorzuheben ist.
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    Ultrarotspektren von Tellursäuren, Telluraten und Antimonaten (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 161-170 
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    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The infrared spectra of some telluric acids, tellurates and antimonates are measured. The constitution of these compounds is discussed.
    Notes: Es werden die Ultrarotspektren der Verbindungen H6TeO6, (H2TeO4)x, Na2H4TeO6, K2H4TeO6 · 3 H2O, Na[Sb(OH)6], KSbO3 · 2,2 H2O, Na2HSb3O9 · 4 H2O, K2HSb3O9 · 5 H2O, NaSbO3 und KSbO3 im Bereich 400-4000 cm-1 angegeben und ausgedeutet. Die Konstitution dieser Verbindungen wird diskutiert.
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    Die Schwingungsspektren von verschiedenen Cyanaten des Siliciums (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 194-204 
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    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: From infrared spectra in the NaCl-region and Raman spectras of several cyanates of silicon (see „Inhaltsübersicht°“), the isocyanate structure for all these compounds has been demonstrated. There is a small multiple bond character of Si-N-bonds.
    Notes: Es wurden die Infrarot-Spektren im NaCl-Bereich und die Raman-Spektren von (CH3)3Si(NCO), (CH3)2Si(NCO)2, CH3Si(NCO)4, Si(NCO)4 und Si2O(NCO)6 aufgenommen und eine Zuordnung zu den Grundschwingungen dieser Molekel vorgenommen. Für alle Verbindungen konnte die Isocyanatstruktur spektroskopisch nachgewiesen werden, auch für die in der Literatur mit normaler Cyanatstruktur beschriebene Verbindung. Bei dieser handelt es sich um ein Gemisch von Si(NCO)4 + Si2O(NCO)6. Weiterhin ergab sich aus den Spektren der Isocyanate, daß die Si-N-Bindungen einen geringen Mehrfachbindungsanteil haben.
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    Farbe und Konstitution bei anorganischen Feststoffen. II. Die Lichtabsorption des zweiwertigen Nickels in oxydischen Koordinationsgittern (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 159-174 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The influence of coordination number, lattice expansion, and decreasing degree of symmetry or distortion of the coordination polyhedron on the light absorption of Ni2+-ions in various oxides (see „Inhaltsübersicht°“) have been studied by spectrophotometric determination of powder remission.As in the case of Co(II)-containing oxides, the main absorption band is shifted toward the UV-region by raising the coordination number from 4 to 6. Displacement toward the red sometimes occurs on lattice expansion.Stronger shiftings to the red and high intensities of absorption have been observed when the decrease of point symmetry of coordination polyhedron is accompanied by stronger distortion.The ranges of homogeneity in the system Zn2SiO4/Ni2SiO4 have been determined spectrometrically.
    Notes: Durch spektralphotometrische Bestimmung der Remission von Pulvern wurde die Abhängigkeit der Lichtabsorption des Ni2+ von folgenden Faktoren untersucht: 1. Koordinationszahl (Ni0,1Mg0,9Al2O4, KZ = 4, Ni0,1Mg0,9O, KZ = 6) 2. Gitterdehung (Ni0,1Mg0,9Al2O4 → Ni0,1Mg0,9Ga2O4), (Ni0,1Mg0,9O → Ni0,01Mg0,69Zn0,3O), (Ni0,1Mg0,9TiO3 → Ni0,1Cd0,9TiO3) 3. Symmetrieerniedrigung bzw. Verzerrung des Koordinationspolyeders (Ni0,1Zn1,9SiO4, Ni0,01Zn0,99O), (Ni0,25Mg1.75SiO4, Ni0,1Mg0,9TiO3). Wie im Fall des Co2+ bewirkt hier die Erhöhung der Koordinationszahl von 4 auf 6 bei einer Eigensymmetrie des Koordinationspolyeders Td bzw. Oh eine UV-Verschiebung der Hauptabsorptionsbanden. Eine Gitterdehnung kann, insbesondere bei einfachen Gittern, eine Rotverschiebung bewirken. Eine Erniedrigung der Punktsymmetrie des Koordinationspolyeders hat nur dann eine stärkere Rotverschiebung und Erhöhung der Absorptionsintensität zur Folge, wenn damit gleichzeitig eine stärkere Verzerrung des Koordinationsoktaeders verbunden ist. Das System Zn2SiO4/Ni2SiO4 wurde spektralphotometrisch untersucht und die Grenzen der Homogenitätsgebiete aus dem Vergleich der Spektren ermittelt.
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    Über Schwermetallamide. IX. Hydroxokobalt(III)-amide (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 175-193 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Two isomeric hydroxy-cobalt(III)-amides, I and II, of the composition [Co(NH2)2OH]n have been prepared by interaction of KNH2 with [Co(NH3)5OH](NO3)2 and [Co2(NH3)8(OH)2]X4 (X = NO3- or SCN-), respectively, in liquid ammonia. The reactions of the amorphous amides, the structures of which are discussed, with a surplus of KNH2 and NH4NO3 in liquid ammonia and the thermal decomposition of II have been studied.The reaction between [Co(NH3)6](NO3)3 and KNH2 yields {[Co2(NH2)5NH3]n(NO3)n}.
    Notes: Durch Umsetzung von [Co(NH3)5(OH)](NO3)2 (I) und [Co2(OH)2(NH3)8]X4 (II) (X = NO3 oder SCN) mit KNH2 in flüssigem NH3 wurden zwei strukturisomere Mono-hydroxokobalt(III)-amide {Co(NH2)2OH}n (III bzw. IV) als unlösliche, amorphe Niederschläge erhalten. Das aus II gewonnene m̈-Monohydroxokobalt-(III)-amid (IV) besitzt noch die Di-m̈-hydroxogruppierung, sofern die Fällung bei tiefen Temperaturen (-20° C) erfolgt. Beide Verbindungen III und IV sind als Derivate des Kobalt(III)-amids zu betrachten und sind wie dieses mehr oder weniger hochpolymer. Unter Berücksichtigung des Strukturprinzips ist III als poly-m̈-Hydroxo-di-m̈-amino-kobalt(III) und IV als poly-[Di-m̈-hydroxo-m̈-amino-kobalt-tri-m̈-amino-kobalt(III)] zu bezeichnen. Der aus I resultierende Bodenkörper (III) reagiert mit NH4NO3 in flüssigem NH3 unter additiver Salzbildung zu {[Co2(OH)2NH2(NH3) 6]n(NO3)3n} (V), einem amorphen Nitrat, mit polymerem Kation, das noch alle OH-Gruppen enthält. IV reagiert ebenfalls mit NH4NO3 unter additiver Salzbildung, jedoch unter Eliminierung der Hälfte aller OH-Gruppen zu {[Co2(OH)(NH2)2(NH3)6]n(NO3)3n} (VIII). Mit KNH2 erfolgt ein Austausch von OH gegen NH2 sowohl in III als auch in IV unter Bildung von KOH. Bei der Reaktion von II mit KNH2 konnte ein definiertes Zwischenprodukt {[Co2(OH)2(NH2)3(NH3)2]n(NO3)n} (VI) gefaßt werden. Ein analoges; um 1 NH3 ärmeres Zwischenprodukt {[Co2(NH2)5(NH3)]n(NO3)n} (VII) - die OH-Gruppen sind durch NH2 ersetzt - entsteht auch bei der Reaktion von [Co(NH3)6](NO3)3 mit KNH2 in flüssigem NH3. Der thermische Abbau von IV führt unter NH3- und N2-Abspaltung schließlich zu CoO. Eine Wasserabspaltung wurde hierbei nicht beobachtet.
    Additional Material: 3 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000308
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    Über ein Siliciumphosphid Si2P (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 205-209 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The compound Si2P is formed at 450 °C from SiH4 and PH3, if the starting gas mixtures are containing SiH4 and PH3 in the ratio of 1 : 1 or 1 : 2. Si2P is a blue black non-crystalline substance. At 600 °C Si2P decomposes into Si and SiP as recognized from X-ray diagrams and IR-spectra. SiP formed from Si2P is identical with that prepared by Biltz1) from its elements.
    Notes: Aus SiH4 und PH3 bildet sich um 450 °C die Verbindung Si2P, wenn man von Gasmischungen SiH4:PH3 = 1 : 1 oder 1 : 2 ausgeht. Si2P ist ein blauschwarzes, röntgenamorphes Produkt. Um 600 °C zerfällt es in Si und SiP, wie aus den Röntgendiagrammen und den IR-Aufnahmen zu erkennen ist. Das aus dem Si2P entstehende SiP ist mit dem von Biltz1) aus den Elementen dargestellten SiP identisch.
    Additional Material: 3 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000310
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    Masthead (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959) 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593000501
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    Spektroskopische Untersuchungen an Siliciumverbindungen. X. Schwingungsspektren und Struktur des Tetramethyl-cyclo-disilthians und des Hexamethyl-cyclo-trisilthians (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 210-220 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The Raman and infrared spectra of [(CH3)2SiS]2 and [(CH3)2SiS]3 are reported and the frequencies are assigned as far as possible. [(CH3)2SiS]2 has the symmetrie D2h with a planar ring. The ring of [(CH3)2SiS]3 is puckered. The most probable symmetrie is here Cs (cis structure). The correlation of the SiXSi angle and the ring structure of siloxanes, silazanes and silthianes is discussed.
    Notes: Die Raman- und IR-Spektren des [(CH3)2SiS]2 und [(CH3)2SiS]3 werden mitgeteilt und die Frequenzen soweit wie möglich den einzelnen Schwingungsformen zugeordnet. Für das [(CH3)2SiS]2 ergibt sich eine ebene Ringstruktur nach D2h. Der Ring des [(CH3)2SiS]3 ist gewellt und hat höchstwahrscheinlich Cis-(Wannen-)Struktur, Punktgruppe Cs. Der Zusammenhang zwischen SiXSi-Winkel und Ringstruktur der Siloxane, Silazane und Silthiane wird diskutiert.
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000311
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    Das Verhalten von Amidophosphaten beim Erhitzen (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 221-224 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Mixtures of amides of imidophosphoric acids with the composition PnOn(NH)n-1 · (NH2)n+2 are formed from OP(NH2)3 by heating at 100° C. - NaPO2)2 respectively Na2PO3NH2 looses all nitrogen by heating in the air at 900° resp. 1000° C and forms glassy (NaPO3)x resp. Na4P2O7.
    Notes: Amidophosphate werden beim Erhitzen infolge intermolekularer Abspaltung von Ammoniak zu Imidopolyphosphaten kondensiert. Aus Phosphoroxytriamid entstehen bei etwa 100° Gemische von Imidophosphorsäureamiden der Formel PnOn(NH)n-1(NH2)n+2 mit n = 2…5. Naturiumdiamidophosphat bzw. Natriummonoamidophosphat geben beim Erhitzen an der Luft auf 900° bzw. 1000° den gesamten Stickstoff ab und gehen in glasiges Natriumpolyphosphat (NaPO3)x bzw. Natriumdiphosphat über.
    Additional Material: 1 Tab.
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    URL: http://dx.doi.org/10.1002/zaac.19593000312
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    Eine Abgekürzte Schreibweise für Phosphorsäuren niederer Oxydationszahl Vorbemerkung zu den folgenden Mitteilungen (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 225-228 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: An abbreviated nomenclature is proposed for acids of phosphorus with lower oxydation number.
    Notes: Es wird eine abgekürzte Bezeichnungsweise für Phosphorsäuren niederer Oxydationszahl vorgeschlagen.
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    URL: http://dx.doi.org/10.1002/zaac.19593000502
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    Über Phosphorsäuren niederer Oxydationszahl. II. Über die \documentclass{article}\pagestyle{empty}\begin{document}${\rm (- P -)}_{\rm 6}$\end{document}-Ringsäure (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 237-249 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Red phosphorus suspended in alkali hydroxyde solutions reacts with hypohalogenites under formation of salts of an acid \documentclass{article}\pagestyle{empty}\begin{document}${\rm (- P -)}_{\rm 6}$\end{document}. The oxidation number of phosphorus in this compound is 3+. The phosphorus atoms are linked together by P - P bonds. The compound has a ring structure.
    Notes: In Alkalihydroxydlösungen suspendierter roter Phosphor reagiert mit Hypohalogeniten unter Bildung von Salzen einer \documentclass{article}\pagestyle{empty}\begin{document}${\rm (- P -)}_{\rm 6}$\end{document}-Ringsäure. Die Oxydationszahl des Phosphors in der Verbindung ist 3+; die Phosphoratome sind über P - P-Bindungen miteinander verknüpft. Die Verbindung hat Ringstruktur.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000504
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    Über Phosphorsäuren niederer Oxydationszahl. III. Über die \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 3} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}Säure (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 250-260 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The preparation of salts of an acid of phosphorus in which 3 phosphorus atoms are linked together in a straight chain is described. The acid is prepared from oxidates of the acid \documentclass{article}\pagestyle{empty}\begin{document}${\rm (} - \mathop {\rm P}\limits^{\rm 3} -)_6$\end{document}, from oxidates of red phosphorus and from hydrolyzates of phosphorus tribromide.
    Notes: Die Herstellung von Salzen einer Säure des Phosphors, in der 3 Phosphor-Atome linear miteinander verbunden sind, aus Oxydaten der \documentclass{article}\pagestyle{empty}\begin{document}${\rm (} - \mathop {\rm P}\limits^{\rm 3} -)_6$\end{document}-Ringsäure, aus Oxydaten des roten Phosphors und aus Hydrolysaten des Phosphortribromids wird beschrieben.
    Additional Material: 3 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593000505
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    Über Phosphorsäuren niederer Oxydationszahl. I. Über Oxydation und Hydrolyse der \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 2} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure und der \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 300 (1959), S. 229-236 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid is stable even towards 80% alkali hydroxide at 200°C. It is transformed to orthophosphate in molten anhydrous alkali hydroxide. The \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 2} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid is also very stable towards alkali hydroxide. Under rigorous conditions it is oxidized to \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid with yields up to 85% of theory under formation of hydrogen. High yields of \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid can also be obtained by reacting iodine with \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 2} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid in mineral acid solution. Copper catalyzed oxidation of \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-acid by hypobromite in alkaline solution leads to mixtures of ortho- and pyrophosphate.
    Notes: Die \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure ist sogar gegen 80proz. Alkalihydroxyd bei 200°C beständig, erst schmelzendes wasserfreies Alkalihydroxyd verwandelt zu Orthophosphat. Auch die \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 2} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure ist gegen Alkalihydroxyd sehr beständig; bei verschärften Bedingungen wird sie mit Ausbeuten bis zu 85% unter Wasserstoffentwicklung zur \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure oxydiert. Auch bei der Einwirkung von Jod auf die \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 2} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure in mineralsaurer Lösung können hohe Ausbeuten der \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure erhalten werden. Die durch Kupfer katalysierte Oxydation der \documentclass{article}\pagestyle{empty}\begin{document}$\mathop {\rm P}\limits^{\rm 4} {\rm - }\mathop {\rm P}\limits^{\rm 4}$\end{document}-Säure in alkalischer Lösung durch Hypobromit führt zu Gemischen von Ortho- und Pyrophosphat.
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    Über Peroxyantimonate (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 316-322 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Solutions of antimonates give with H2O2 peroxy-antimonates. These are amorphous, polymeric, insoluble substances. The approximate composition of some of these compounds is KSbO4 · 1,7 H2O, NaSbO4 · 2 H2O, KSbO4 · 1,8 H2O2 and K2HSb3O12 · 3,5 H2O. The constitution of the peroxy-antimonates is discussed with help of their infrared spectra.
    Notes: Aus Lösungen von Kaliumantimonat entstehen mit H2O2 Peroxyantimonate. Diese sind amorphe, schwer lösliche, polymere Substanzen. Isoliert wurden unter anderem Verbindungen der annähernden Zusammensetzung KSbO4 · 1,7 H2O NaSbO4 · 2 H2O, KSbO4 v 1,8 H2O2 und K2HSb3O12 · 3,5 H2O. Die Konstitution der Peroxyantimonate wird an Hand ihrer Ultrarotspektren diskutiert.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/zaac.19593010514
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    Über die Hydroxylgruppen an der Oberfläche des Amorphen Siliciumdioxyds „Aerosil“ und ihre Reaktionen (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 326-335 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Reactions of surface hydroxyl groups have been investigated with finely divided amorphous silica (Aerosil). The hydroxyl groups react with calcium hydroxide; esters are formed by reaction with alcohols and diazomethane. Heating with thionyl chloride leads to substitution by chlorine. This reaction is especially suited for the quantitative determination of hydroxyl groups bound to silica surfaces.With lithium phenyl, chlorine bonded to surface silicon atoms can be substituted by phenyl groups.Quantitative determinations show that for Aerosil the number of surface hydroxyl groups is lower than the maximum amount estimated for silica surfaces; their surface concentration varied for different batches.
    Notes: An Aerosil, einem feinteiligen amorphen Siliciumdioxyd-Präparat der Degussa, wurden Umsetzungen mit den an der Oberfläche gebundenen Hydroxylgruppen durchgeführt. Die Hydroxylgruppen reagieren mit Calciumhydroxyd; mit Alkoholen und mit Diazomethan lassen sie sich verestern. Bei der Einwirkung von Thionylchlorid werden sie durch Chlor ersetzt. Diese Reaktion ist zur quantitativen Bestimmung der an Siliciumdioxyd-Oberflächen gebundenen Hydroxylgruppen besonders gut geeignet.Bei der Umsetzung mit Lithiumphenyl wird das am Silicium gebundene Chlor seinerseits durch Phenylgruppen ersetzt.Die quantitative Verfolgung der Reaktionen ergab, daß das Aerosil nicht die maximal mögliche Zahl oberflächenständiger Hydroxylgruppen besitzt. Ihre Menge pro Flächeneinheit ist vom jeweils gelieferten Muster abhängig.
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    URL: http://dx.doi.org/10.1002/zaac.19593010516
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    Bariumfluoroborat (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 336-338 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Pure anhydrous Ba(BF4)2 has been prepared by interaction between BaF2 and BF3 · 2 H2O and purification of the crude reaction product by means of acetone.The solubilities of Ba(BF4)2 in H2O, acetone, methanol, and ethanol have been determined.
    Notes: Das reine wasserfreie Ba(BF4)2 wird durch Umsetzung von BaF2 mit BF3 · 2 H2O und Behandlung des entstandenen Rohsalzes mit Aceton gewonnen.Die Löslichkeit von Ba(BF4)2 in Wasser, Aceton, Methanol und Äthanol wird bestimmt.
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    URL: http://dx.doi.org/10.1002/zaac.19593010517
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    Über die Hydrolyse des Antimon(V)-säureäthylesters (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 339-342 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Sb(OC2H5)5 is hydrolized on action with ½ mol of water yielding the dimeric ester (C2H5O)4Sb—O—Sb(OC2H5)4. By larger quantities of water polymeric chains and net works are formed.
    Notes: Durch Hydrolyse von Sb(OC2H5)5 mit einem halben Mol Wasser entsteht die kondensierte Verbindung (C2H5O)4SbOSb(OC2H5)4. Größere Mengen an Wasser führen zu ketten förmigen und vernetzten Produkten.
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    URL: http://dx.doi.org/10.1002/zaac.19593010518
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    Reaktionen und Gleichgewichte in Alkalihydroxydschmelzen. III. Peroxydgleichgewichte (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 285-301 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The formation of alkali peroxides by reaction between molten alkali hydroxides and oxygen in the presence of water vapor at temperatures of 410 and 510°C has been investigated. Maximum yields of peroxides obtained in dry pure oxygen at 410°C are to be seen in „Inhaltsübersicht“.At definite low pressures of water vapor reproducible peroxide yields have been observed. From the dependence of equilibrium values from oxygen and water vapor pressures there is evidence that in molten NaOH mainly Na2O2 is formed, whereas in KOH, RbOH and CsOh the hyperoxides KO2, RbO2, and CsO2, respectively are the main reaction products.
    Notes: Es wurde das zur Bildung von Alkaliperoxyden führende Gleichgewicht zwischen Alkalihydroxydschmelzen und Sauerstoff in Gegenwart von Wasserdampf bei 410° und 510°C näher untersucht. In trockenem, reinem Sauerstoff wurden bei 410°C maximal folgende Mengen Peroxyd gebildet:.Während es sich bei diesen Zahlen um die in trockenem Sauerstoff, also bei undefiniertem Wasserdampfpartialdruck praktisch erreichbaren Höchstwerte handelt, stellen sich bei geringen Wasserdampfpartialdrucken gut reproduzierbare Gleichgewichte im Laufe von 6 - 15 Stunden ein. Identische Gleichgewichtswerte konnten auch von der anderen Seite her, ausgehend von KO2 erhalten werden.Die Abhängigkeit der Gleichgewichtswerte vom Sauerstoffpartialdruck und Wasserdampfpartialdruck wird an Hand logarithmischer Diagramme diskutiert. Man gelangt dabei zu dem Schluß, daß die NaOH-Schmelzen das Peroxyd Na2O2 gelöst enthalten, während bei den KOH-, RbOH- und CsOH-Schmelzen die Hyperoxyde KO2, RbO2 und CsO2 überwiegen.
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    Zur Chemie der kondensierten Phosphate und Arsenate. XXII. Die Bedeutung der Kationen bei der Papierchromatographie der kondensierten Phosphate (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 298 (1959), S. 316-336 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: In paper chromatography of condensed phosphates in acid medium the presence of little quantities of ammonia is necessary. For the explanation of this fact, which was not previously understood, it has been shown that ammonia can be replaced by other monovalent cations. The dependence of chromatographic separation on the cation type and cation concentration has been, therefore, investigated. Furthermore, it has been demonstrated that cations migrate independent of the phosphate anions. However, the presence of cations is necessary in order to differentiate between the solubilities of condensed phosphates by virtue of their molecular weight and their constitution.
    Notes: Bei der Papierchromatographie kondensierter Phosphate in saurem Medium erwies sich die Anwesenheit kleiner Mengen von Ammoniak als notwendig. Zur Aufklärung dieser bisher unverstandenen Tatsache wird gezeigt, daß das Ammoniak durch andere einwertige Kationen ersetzt werden kann, die Trennwirkung in Abhängigkeit von Kationenart und -menge untersucht und außerdem nachgewiesen, daß die Kationen unabhängig von den Phosphatanionen wandern. Die Gegenwart der Kationen ist aber notwendig, um die Löslichkeit der kondensierten Phosphate in Abhängigkeit von ihrem Molekulargewicht und ihrer Konstitution zu differenzieren.
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    Professor Dr. phil. Otto Schmitz-DuMont (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 1-2 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990102
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  • 95
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    Studies on the composition and properties of metal ferrocyanogen complexes. II. Physico-chemical studies on the Nature and Composition of Chromous Ferrocyanide (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 301 (1959), S. 350-354 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Die Rektion zwischen CrCl2 und K4Fe(CN)6 ist mittels potentiometrischer, konduktometrischer und amperometrischer Titrationen untersucht worden. Mit den ersten beiden Methoden wurde die Bildung von K2CrFe(CN)6 und Cr2Fe(CN)6 nachgewiesen; die amperometrische Titration gab nur Hinweise für die Existenz der ersteren Verbindung. Durch die Adsorptionsfähigkeit der Verbindungen entstehen Fehler, die in Gegenwart von Alkohol geringer sind als in rein wäßrigem Medium.
    Notes: Potentiometric, conductometric and amperometric titrations have been carried out between CrCl2 and K4Fe(CN)6 with varying concentrations of the reagents in aqueous and aqeous-alcoholic media. While evidence for the formation of both K2CrFe(CN)6 and Cr2Fe(CN)6 was obtained from the first two methods, the amperometric titrations gave evidence only for the formation of K2CrFe(CN)6. From the discrepancies in the titre values (theoretical and determined), evidence for the role of adsorption in influencing the composition is obtained. The titre values approach the theoretical when measurements are done in presence of alcohol.
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593010520
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  • 96
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    Über Subchalkogenidphasen des Titans (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959), S. 17-36 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The systems TiS—Ti, TiSe—Ti, and TiTe—Ti have been investigated by X-ray analysis.The range of homogeneity of the TiX-phases in all these systems extends to the composition of TiX0.8. In the systems TiS—Ti and TiSe—Ti, a Ti3X2-phase with a limit composition of TiX0.5 follows, whereas in the tellurium system a Ti2Te-phase (limit composition TiTe0.25) occurs. In the case of both TiSe and TiTe, a new hexagonal modification has been manifested; furthermore, the TiSe-phase crystallizes in a third lattice being trigonal. These new modifications are the stable forms of the phases TiSe and TiTe representing overstructures of the NiAs-type. The structures of other phases are: \documentclass{article}\pagestyle{empty}\begin{document}$$ \begin{array}{l} {\rm Ti}_{\rm 3} {\rm S}_{\rm 2} \,\,{\rm WC - type;} \\ {\rm Ti}_{\rm 3} {\rm S}_{\rm 2} \,\,\,{\rm NiAs - type;} \\ {\rm Ti}_{\rm 2} {\rm Te}\,\,{\rm tetragonal}\,{\rm unknown}\,{\rm structure}{\rm.} \\ \end{array} $$\end{document}
    Notes: Es wurden die Systeme TiS/Ti, TiSe/Ti und TiTe/Ti röntgenographisch untersucht. Der Homogenitätsbereich der TiX-Phasen erstreckt sich in allen Systemen etwa bis zur Zusammensetzung TiX0,8. In den Systemen TiS/Ti und TiSe/Ti folgt eine Ti3X2-Phase mit einem Homogenitätsbereich bis zur Zusammensetzung TiX0,5, in dem System TiTe/Ti eine Ti2Te-Phase mit einem Homogenitätsbereich bis zur Zusammensetzung TiTe0,25. Die Löslichkeit der Chalkogene im Titanmetall nimmt zum Tellur hin stark ab.Bei der TiSe- und TiTe-Phase wurde außer der bereits bekannten NiAs-Form eine weitere hexagonal kristallisierende Modifikation festgestellt, bei der TiSe-Phase noch eine dritte trigonal kristallisierende. Beide neu gefundenen Modifikationen sind die stabilen Formen dieser Phasen und stellen Überstrukturen des NiAs-Typs dar. Die Ti3S2-Phase kristallisiert im WC-Typ, die Ti3Se2-Phase im NiAs-Typ und die Ti2Te-Phase in einer tetragonalen Struktur unbekannten Typs.
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020104
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  • 97
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    Über die Bildung salzartiger Verbindungen bei der Umsetzung von Antimon(V)-chlorid mit Äthylat (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959), S. 88-102 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: On reaction of SbCl5 with NaOC2H5 salt-like compounds with cation co-ordination number 4 and anion co-ordination number 6 are formed: [SbCla(OC2H5)4-a] [SbClb(OC2H5)6-b]. In polar solvents these substances show electrolytical conductivity and their molecular weights in dilute solution prove complete dissociation into two particles. In nonpolar solvents the compounds are also dissolved but now in a molecular form SbClc(OC2H5)5-c. The latter solutions have no electrolytical conductivity. IR-spectra of the compounds in polar and nonpolar solutions are different from each other.
    Notes: Bei der Umsetzung von SbCl5 mit NaOC2H5 entstehen heteropolare Verbindungen mit 4fach koordiniertem Kation und 6fach koordiniertem Anion: [SbCla(OC2H5)4-a] [SbClb(OC2H5)6-b]. In polaren Lösungsmitteln zeigen diese Substanzen elektrolytische Leitfähigkeit und Molekulargewichte, die in verdünnter Lösung auf vollständige Dissoziation schließen lassen. In unpolaren Lösungsmitteln sind die Verbindungen in homöopolarer Form SbClc(OC2H5)5-c gelöst. Diese Lösungen zeigen nur sehr geringe Leitfähigkeit. Die Infrarotspektren der Verbindungen in polaren und unpolaren Lösungen unterscheiden sich stark voneinander.
    Additional Material: 13 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020109
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    Masthead (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 302 (1959) 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19593020301
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  • 99
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    Bildungswärme von La2O3 und La(OH)3 (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 227-231 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: The heat of reaction 2 La + 1,5 O2 = La2O3 was determined to 446 ± 2 kcal/Mol by measuring the heats of solution of La2O3 in 0,1 n HCl and comparing it with the heat of solution of La in 0,1 n HCl by BOMMER and HOHMANN. The older values of the heat of combustion were discussed and the mistake of the extreme value of Roth cleared up.The heat of hydratation 1/2 La2O3 + 1,5 H2O = La(OH)3 was determined to 20,2 ± 0,7 kcal/Mol by measuring the heat of solution of cristallised La(OH)3 in 0,1 n HCl.
    Notes: Die Bildungswärme von La2O3 wurde durch vergleichende Messung der Lösungswärmen von La2O3 und La in 0,1 n HCl zu 446 ± 2 kcal/Mol bestimmt und mit drei älteren direkten Messungen der Verbrennungswärme verglichen. Bei dem abnorm hohen Wert von ROTH (539) wurde eine Fehlerquelle nachgewiesen.Die Hydratisierungswärmen von La2O3 wurde durch vergleichende Messung der Lösungswärme von krist. La(OH)3 und La3O2 zu 20,2 ± 0,7 kcal/Mol bestimmt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990316
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    Bildung siliciumorganischer Verbindungen. VI. Darstellung ringförmiger Siliciummethylenverbindungen (Cyclocarbosilane) aus Si(CH3)4 (1959)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 299 (1959), S. 232-240 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: 1. Higher molecular siliconmethylene compounds have been prepared by thermic decomposition of Si(CH3)4. The composition of the reaction mixture relies on their stay period in the reaction tube. The experimental conditions of the forming of higher boiling and meltable silmethylene compounds are described.2. A number of compounds have been isolated from the reaction mixture, see „Inhaltsübersicht“. The common structure of the compounds has been found to consist of sixmembered rings which have a skeleton of alternate silicon and carbon atoms.
    Notes: 1. Aus Si(CH3)4 lassen sich durch thermische Zersetzung höhermolekulare Siliciummethylenverbindungen darstellen. Die Zusammensetzung der Reaktionsprodukte ist von ihrer Verweilzeit im Reaktionsgefäß abhängig. Es werden die experimentellen Bedingungen zur Darstellung höhersiedender und schmelzbarer Siliciummethylenverbindungen angegeben.2. Es wurden folgende Verbindungen aus dem Reaktionsgemisch isoliert. Si2C6H18, Si2C7H20, Si3C8H22, Si3C9H24, Si4C10H26, Si4C11H28, Si5C13H34, Si6C14H36, Si7C18H46, Si8C20H50, Si8C24H66, Si9C27H74. Die Si-Atome sind stets über je ein C-Atom verbunden. Das Gemeinsame im Aufbau der Verbindungen mit 3 und mehr Si-Atomen besteht darin, daß sie aus Sechsringen mit drei Si- und drei C-Atomen bestehen, die im Ring abwechselnd angeordnet sind.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19592990317
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