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  • Chemical Engineering  (583)
  • Aircraft Stability and Control  (73)
  • Analytical Chemistry and Spectroscopy
  • 1955-1959  (656)
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  • 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
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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
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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
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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
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    Physical and thermodynamic properties of trifluoromethane (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 125-129 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 7 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050126
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  • 59
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    Thermodynamic properties of acetylene (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 17-19 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The derived thermodynamic properties of acetylene have been determined over a temperature range of 32 to 500°F. and up to pressures of 2,000 lb./sq. in. abs. The data were calculated from vapor pressure, volumetric, and heat-capacity data by the use of rigorous thermodynamic relationships. The calculated data were found to be internally consistent. The enthalpy values are believed to be accurate within ±1.0 B.t.u./lb. and the entropy values to ±0.001 B.t.u./(lb.)(°R.).
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050105
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  • 60
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    Equilibria in the hydration of ethylene at elevated pressures and temperatures (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 10-16 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Values of equilibrium composition for the hydration of ethylene to form ethanol have been calculated for a series of elevated pressures and temperatures by using equilibrium data available from previous low-pressure studies. To obtain satisfactory agreement between these values and those measured experimentally, it is essential (1) to take into account the formation of ethyl ether and (2) to use available vapor-liquid equilibrium data for the binary ethanol-water system at elevated temperatures, instead of the standard “mixture rules” often employed.Thermochemical data and low-pressure equilibrium data for both the ethylene hydration and ether formation reactions are critically reviewed. Experimentally measured values for the equilibrium concentrations of ethanol and ether in the liquid phase at 221°C. and 273 atm., with dilute sulfuric acid used as catalyst in a lined rocking-bomb reactor, are presented.
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050104
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  • 61
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    Nonequilibrium thermodynamics: A survey (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 20-25 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: This paper presents a review of the field of thermodynamics of irreversible processes. The three essential steps in the use of this form of thermodynamics are the calculation of the entropy production, the setting up of the linear phenomenological equations, and the use of the Onsager reciprocal relation. The most important applications are to the transport processes, especially to the coupling phenomena which occur when two or more such processes take place in the same system.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050106
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  • 62
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    Simplified calculation of chemical equilibria in hydrocarbon systems containing isomers (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 26-28 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An improved method is presented for handling isomer groups in the calculation of chemical equilibria in complex hydrocarbon mixtures. The new method reduces the number of simulataneous equations involved and makes practical the rigorous calculation of any hydrocarbon system for which free-energy data are available, no matter how complex.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050107
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  • 63
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    Compressibility of n-hexane (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 29-30 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Although a considerable amount of work has been done on the compressibility of n-hexane, it has been impossible until now to compare or evaluate the work of the various investigators. There has also been a serious lack of information in the region above the critical temperature. It is the purpose of this work to make an extensive study of temperatures of 240° to 300°C. and of pressures up to 225 atm. in order to provide the lacking information and to overlap with the work of other investigators so that a proper evaluation of their work may be made.
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050108
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  • 64
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    Control-system design for a chemical process by the root-locus method (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 30-36 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: This paper illustrates the application of the root-locus method in the design of a control system for a theoretical stirred-tank reactor. The merits of control by measuring reactor concentration or temperature were considered at both an unstable and stable steady state reactor condition. The modes of control studied were proportional, proportional-integral, and proportional-integral-rate.
    Additional Material: 18 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050109
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  • 65
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    Low-temperature vapor-liquid equilibria in ternary and quaternary systems containing hydrogen, nitrogen, methane, and ethane (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 46-50 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Experimental data are presented for three ternary systems and the quaternary at pressures of 500 and 1,000 1b./sq. in. abs. and at temperatures of -100° and -200°F. These data along with information in the literature were correlated to give charts of equilibrium ratios as a function of temperature, pressure, and composition.
    Additional Material: 14 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050111
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  • 66
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    The study of flow and reaction rates in turbulent flames (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 37-46 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: It is proposed that measurements of reaction rate as a function of position within turbulent flames be the basis of an approach to the problem of turbulent-flame propagation. As a test of the method, measurements of static pressure, impact pressure, and chemical composition were made at several positions within the burning zones of two simulated ramjet combustion chambers. From these measurements a complete mapping of compositions, velocity components, densities, and static pressures could be carried out. By calculation of the appropriate derivatives of the latter quantities, the differential form of the equation of continuity for the species desired could be solved for net reaction rate as a function of position, turbulent diffusion being neglected. By a similar technique the equation of momentum was used to obtain eddy viscosities. The latter results were used to estimate the effect of turbulent diffusion by assuming a turbulent Schmidt number of unity.It is concluded that the method of attack used is a reasonable approach to the problem of turbulent flame propagation, having a special advantage in that it can be used to discover relationships between the rate of reaction and the patterns of the mean flow.
    Additional Material: 20 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050110
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  • 67
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    Performance of packed columns: V. Effect of solute concentration on gas-phase mass transfer rates (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 290-294 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In a determination of the effect of solute concentration on gas-phase mass transfer rates carbon tetrachloride was vaporized at three different concentration levels in a short 4.0-in.-diameter column packed with 0.5-in. Raschig rings.The experimental data indicate that previous mass transfer correlations should be modified to include a term (PBM/PT)2/3 and that the Schmidt number should be evaluated at average film conditions.The correlation found is suitable for predicting gas-phase mass transfer coefficients which can be combined with effective interfacial areas reported previously to obtain volumetric mass transfer coefficients for any gas-liquid-solute system.
    Additional Material: 10 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050308
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  • 68
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    Multicomponent distillation on a large digital computer: II. Generalization with side-stream stripping (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 295-300 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The problem of multicomponent distillation is considered for a column with an arbitrary number of feed streams and an arbitrary number of side-stream withdrawals. The overheads from the side-stream strippers are admitted to the column, introducing the inert stripping medium into the main column. Provisions are made in the calculations for complete heat balancing, inert injection, and internal reflux cooling. The method of computation is that of a previous paper involving the component-by-component technique. Calculations are made on the main column and give first approximations to the side-stream compositions; stripper calculations are then initiated. An alternating procedure is instituted between the main column and the strippers, the successive iterations continuing until a preassigned accuracy in the desired quantities is reached. An extensive numerical problem is worked.
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    Particulate fluidization and sedimentation of spheres (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 310-314 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Particulate fluidization and sedimentation data were taken over the Reynolds number range of 0.005 to 1,800 by means of glass spheres in both water and ethylene glycol. Porosities for each series of measurements varied from about 0.50 to 0.91 and larger. The closely sized samples of spheres used were obtained by grinding between glass plates. The data for Reynolds numbers up to about 0.5 are in excellent agreement with the laminar theory of Ruth and the porosity function from Ruth's theory gave a satisfactory correlation of all the data, both laminar and turbulent.
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    Formation of gas bubbles at submerged orifices (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 319-324 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The formation of air bubbles at constant pressure at submerged orifices was investigated for several liquids. The frequency of formation of the bubbles was determined by the use of a stroboscope, and the rate of gas flow was measured with conventional rotameters. Several orifices having diameters ranging from 0.0794 to 0.397 cm. were employed, and the gas flow rate was varied from about 0.1 cc. (at standard conditions)/sec. to about 150 cc./sec. It was found that the formation of bubbles could be correlated with the physical variables of the system by the application of Newton's second law of motion to the bubble at the instant just prior to its release from the orifice.
    Additional Material: 9 Ill.
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    Some aspects of fluid mechanics in chemical engineering (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 331-338 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The prediction of the transfers of momentum, energy, and material is of ever-pressing concern to the engineer interested in process design. Recently developed facts concerning the transport of momentum which are of particular use in predicting transfers of energy and material are reviewed, as well as the background of thermodynamics associated with transport processes. The more elemental relationships pertaining to thermal and material transfer in flowing streams are considered, and some of the interrelations of the transport processes are presented.
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    Reply (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 134-134 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
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    The influence of heat transfer on mass transfer at low pressures (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 135-136 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
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    Reply (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 136-136 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050132
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    Ion exchange resins, by Robert Kunin, John Wiley & Sons, Inc. 466 pages (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 10M 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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    URL: http://dx.doi.org/10.1002/aic.690050135
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    Studies of the cation exchange system Fe+++-H+: I. Equilibrium studies (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 391-393 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Equilibrium data are presented for the exchange of Fe+++ and H+ on a sulfonated polystyrene exchanger. The data cover solution concentrations from 0.05 N to 2 N in total cation for solutions having either nitrate or perchlorate ion as the common anion. The nitrate system shows irregular behavior because of complex ion formation, but for composition where such behavior is absent the equilibrium data can be correlated by equations based on the law of mass action. Equilibrium compositions for the perchlorate system can be correlated over the entire range studied by a single equation based on the law of mass action. Methods based on the law of mass action are presented for correlating or predicting equilibrium compositions for both systems.
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    The vapor-phase catalytic hydration of ethylene oxide to glycols (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 496-501 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The vapor-phase reaction between ethylene oxide and water to form glycols has been carried out under a wide range of conditions with particles of polystyrene-sulfonic acid ion exchange resins used as catalysts. The rates observed appeared to be directly proportional to the product of the partial pressure of ethylene oxide and the amount of water sorbed by the resin. By use of the Brunauer, Emmett, and Teller equation to describe the amount of water sorbed by the resin, the experimental data were correlated over a sixty-fold range of reaction rates with a mean deviation of 15%.To obtain data of value in elucidating reaction mechanisms, the reactor was usually run under “differential” conditions, that is low conversions. However in a few runs conversions of as high as 54% were obtained for a contact time of 0.02 sec. The ratio of ethylene glycol to higher glycols (selectivity) obtained varied between 73 and 99% but was usually above 80% under conditions of high conversion. However it could also be reduced forcibly to produce higher glycols as the major product, if desired.
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    Film boiling of Helium I and other liquefied gases on single wires (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 403-406 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Heat transfer coefficients have been obtained for natural-convection film boiling of helium I on single wires with a diameter ranging from 5 to 50 μ. The measurements covered temperature differences of 30° to 1,000 °K. between the heating surface and the saturated liquid under atmospheric pressure. The results are correlated in dimensionless from (Nusselt number vs. the product of the Grashof and Prandtl numbers) and compared with data for nitrogen and measurements of other investigators on film boiling of liquefied gases.
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    Semifluidization: Mass transfer in semifluidized beds (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 407-409 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 6 Ill.
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    Thermodynamic consistency test for multicomponent solutions (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 7S 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050334
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    Liquid-side mass transfer coefficients in packed towers (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 8S 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
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    Plant design and econmics for chemical engineers, Max S. Peters, McGraw-Hill Back Company, Inc., New York (9158). 511 pages. 511.00. (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 412-563 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050403
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    Void fractions in two-phase flow (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 427-432 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Void fractions (fraction of the flow cross-sectional area occupied by the gas phase) have been measured for steam-water flows in an adiabatic, horizontal test section of 0.484 in. I.D. at 400, 600, 800, and 1,000 1b./sq. in. gauge. A comprehensive survey of void data for two-phase concurrent flow is included in the paper, and the data, including the Martinelli and homogeneous flow model predictions, are compared. System characteristics, involving one- and two-component flows in horizontal and vertical test sections with and without heat transfer over a range of flow ratios, total flow rates, and pressure, are too complex, and the data available are neither extensive nor precise enough to warrant the generation of over-all correlations. Use of the void data in correlating two-phase frictional pressure drops is discussed. A model has been presented for the prediction of critical flows based upon the void data, and calculations have been made for steam-water critical flows over a range of critical pressures from 15 to 2,000 1b./sq. in. abs.
    Additional Material: 11 Ill.
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    Some properties of polar substances: A survey (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 436-439 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The current understanding of the macroscopic (bulk) properties of polar substances in terms of molecular theory, or the correlation of them in terms of corresponding-states principles is summarized.
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    Performance of a reciprocating-plate extraction column (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 446-452 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An open type of reciprocating-plate extraction column was developed, and it is proposed that the scaling up of such a column should be straightforward; that is, the height of an equivalent theoretical stage (H.E.T.S.) and the throughput per unit area should be independent of the diameter of the column.Plates having 5/8-in.-diameter holes and 62.8% free space were selected to minimize the resistance to countercurrent flow in the column. With this design low H.E.T.S. values were achieved at throughputs much higher than those reported for other columns. Thus for two systems the present column was shown to require the lowest volume of column to accomplish a given extraction job. Data were obtained in a 3-in.-diameter column on two systems, methyl isobutyl ketone-acetic acid-water and o-xylene-acetic acid-water. Throughputs studied on the first system ranged from 547 to 1,837 gal./hr./sq. ft., and the corresponding minimum H.E.T.S. values achieved were 4.3 and 7.5 in. respectively. For the second system minimum H.E.T.S. values of 7.7 and 9.1 in. were attained at throughputs of 424 and 804 gal./hr./sq. ft. respectively.Extraction column design procedures are discussed. The fabrication of the reciprocating-plate column is relatively simple, and this should encourage its use first in pilot-scale sizes and ultimately in large-scale columns.
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    Liquid-liquid extraction equilibrium data of cobalt nitrate - nickel nitrate - nitric acid solutions (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 76-79 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Studies of the solvent extraction of cobalt and nickel nitrates from aqueous solution would add to the fundamental knowledge of extraction of metal salts. In experiments performed to determine the extractibility of these metals as nitrates from aqueous solutions by organic solvents, normal butanol was found to be the best solvent and gave equilibrium distribution coefficients K for cobalt or nickel nitrate of about 0.3. The presence of nitric acid tended to decrease these at high metal concentrations.In mixtures of the two metals the K value of either metal was found to depend on the total metal concentration. Low separation factors of about 1.3 were obtained. Very high K values of over 5 were obtained for the equilibrium extraction of the nitric acid in the presence of the metal nitrates by the n-butanol an indication of commercial possibilities.
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    Vaporization of superheated drops in liquids (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 458-466 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The work reported in this paper is an outgrowth of an exploratory investigation of the feasibility of spray drying of materials in solution by using direct-contact heat transfer from a hot liquid rather than a gas to vaporize the solvent from the drops. Unexpectedly, it was found that drops suspended in a hot liquid had to be superheated to a very extreme degree in order to initiate vaporization. This effect was of such interest that the investigation was modified to a fundamental study of the vaporization of drops containing no dissolved solids. The results are closely related to problems of bubble formation in boiling, cavitation, and in the evolution of gases from supersaturated solutions. The experimental technique developed in this study is believed to be unique and capable of giving quite accurate data on homogeneous nucleation in superheated drops. After a discussion of the theory of homogeneous nucleation in pure liquids, the theory is extended to the formation of bubbles in superheated drops. The theoretical predictions were found to be in close agreement with the experimental results.
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    Heat transfer by radiation through porous insulations (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 467-474 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Radiant transfer through fibrous and foamed insulating materials was investigated theoretically and experimentally. Transmission measurements were made under isothermal conditions with a black-body source varying from 200° to 800°F. Bulk density and fiber and pore size were also varied. These data were interpreted successfully in terms of a simple theoretical model. The results provide design information and define the contributions of the several mechanisms of transfer.
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    The economic design of mixer-settler extractors (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 474-482 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Relationships are developed for establishing the most economic values of the major variables of a liquid-extraction process, including the concentrations of solute in recycled solvent and rejected raffinate, the solvent-to-feed ratio, and for mixer-settlers certain of the design features. Consideration is given to costs of extraction and solvent recovery, as well as to the value of unextracted solute and lost solvent. For the design of mixer settlers scale-up relationships are developed to permit prediction of the stage efficiency of a large extractor from experimental data taken on a small scale. These are expressed in terms of a scale-up index relating the relative size of the mixer with the volumetric rates of liquid flow. It is shown that the cost of multistage extractor increases with scale up in a different fashion from the stage efficiency, depending upon the scale-up index used. A detailed study of the costs for a typical case led to the development of economic scale-up indexes which, because they cover nearly a fivefold ratio of fixed to operating costs, are of fairly general utility. The common practice of scaling up with equal holding times on the large and small scale is shown to be amply safe from the point of view of stage efficiency to be realized on the large scale but usually uneconomic.Simplification of the complete system of equations permits rapid estimation of the most economic circumstances for any type of countercurrent extractor of which the cost per stage is proportional to Qg.
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    Fluidized-bed heat transfer correlation (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 7M 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050133
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    Unsteady pseudoplastic flow near a moving wall (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 565 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 1 Ill.
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    Center-line value of the eddy viscosity (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 566 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 2 Ill.
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    Reply (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 5D-5D 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050431
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    The dynamics of heat removal from a continuous agitated-tank reactor (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 240-244 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The present investigation is concerned with the dynamic characteristics of a 12-in. diameter continuous agitated-tank reactor vessel. Response of the vessel effiuent temperature to a change in coolant flow rate through an internal cooling surface is the subject of theoretical and experimental study. Experimental data were obtained through the use of frequency and transient response techniques. Studies were made for the passage of vessel-charge fluids with widely differing physical properties. Also data were taken for various conditions of fluid turbulence both inside and outside the internal heat transfer coils. Experimental and theoretical results are graphically compared. Recommendations are presented for the development of theoretical dynamic relationships.
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    Turbulent liquid flow down vertical walls (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 245-248 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Photoggraphic methods have been used to study the behavior of water flowing freely down vertical surfaces under the influence of gravity at Reynolds numbers between 200 and 30,000. The physical appearances of the liquid layers in transitional and fully turbulent flow have been noted. Layer thicknesses have been obtained from high-speed photographs and correlated with liquid Reynolds numbers, the range of experimental data thus being extended into the fully turbulent region. A simple basis of comparison with flow between parallel plates has been developed.
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    Phase equilibria in mixtures of polar and nonpolar compounds: Derived thermodynamic quantities for alcohols and hydrocarbon (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 249-256 
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    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The properties of vapor mixtures and liquid solutions which determine phase equilibria are of special importance in separation processes. They include the vapor-phase imperfections; the liquid-phase activity coefficents; and the excess heat, entropy, and free energy of mixing.Correlation of these properties in nonpolar mixtures is relatively simple, but in mixtures of polar and nonpolar compounds the molecular interactions lead to more complex relations. Semiempirical relations reported earlier (3, 4) have been used to calculate the vapor imperfections and to correlate the liquid-phase activity coefficients.Temperature variations of the activity coefficients can reflect the true heat and entropy effects in solution if sufficient vapor-liquid equilibria are available for a careful and consistent treatment. This is illustrated with binary mixtures of benzene and the n-aliphatic alcohols, methanol to pentanol. The results are compared with calorimetric data available in the literature.The consistent set of cross-correlated coefficients provides a basis for calculating both isothermal and isobaric vapor-liquid equilibria at various conditions for the binaries and for certain ternary and multicomponent mixtures without any additional data.
    Additional Material: 20 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050223
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    Effective diffusivity of packed bed (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 267-268 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: From time to time, A.I.Ch.E. Journal presents translations of certain technical articles written by our Japanese colleagues in their own language. These translations are made by Kenzi Etani, who received his B.S. in chemical engineering in 1953 at the Tokyo Institute of Technology and his M.S. in 1955 at M.I.T. He is associated with Stone & Webster and is an associate member of American Institute of Chemical Engineers. He is also a member of the Society of Chemical Engineers, Japan, and the Japan Oil Chemists' Society. His offer to help break down the language barrier is acknowledged.Abstracts, notation, literature cited, tables, and figure captions not published here appear in English in the original paper. No figure will be reproduced in these translations.The following article was published in Chemical Engineering (Japan), 21, pages 17-25 (1957).
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050226
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  • 98
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    Thermal conductivity of diatomic gases: Liquid and gaseous states (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 367-372 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: After an extensive literature survey the experimental thermal-conductivity data for twelve diatomic gases were utilized to produce an accurate and expedient means of predicting values over extensive ranges of temperature and pressure. Plotting values of k* against TR on logarithmic coordinates produced similarities pointing to the existence of corresponding states behavior for this family of substances with the exception of hydrogen. Because hydrogen cannot be included in a correlation generalized for the diatomic gases, it has been eliminated from this study. Based on atmospheric pressure data, ratios of k*/k*Tc produced a unique relationship with reduced temperature. To include the effect of pressure, residual thermal conductivities were correlated with density for nitrogen and oxygen, the only substances for which high-pressure data exist. These relationships enabled the determination of the thermal conductivity at the critical point. When the value kc = 8.55 × 10-5 cal./sec. cm. °K. for nitrogen was used, au extensive reduced thermal-conductivity correlation was constructed against reduced temperature for parameters of constant reduced pressure. This chart, extending to reduced pressures of 100 and to reduced temperatures of 85, is recommended for the diatomic gases in their gaseous and liquid states.The developed correlation reproduces experimental nitrogen data to within 1.39%. For the other diatomic gases experimental agreement extends from 1.00 to 3.20%. Such agreement indicates that this correlation is more reliable for the diatomic gases than are other generalized plots presented in the literature.
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050322
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  • 99
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    Continuous stirred tank reactors: Designs for maximum conversions of raw material to desired product. Homogeneous reactions (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 384-390 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: It is shown in a series of illustrative examples how the conversion efficiency of many reactions can be markedly affected by the type of reactor used, even though the temperatures, catalyst, and basic kinetics are already fixed by the chemistry of the process.For such purpose graphical and analytic criteria are developed which permit the selection of a continuous stirred tank or tubular reactor system to obtain the most advantageous conversion of raw material to desired product. When a continuous stirred tank reactor process is preferable, the optimum number of reactor stages for maximum conversion is one. An example is given of a case where a combination of a continuous stirred tank and a tubular reactor is advantageous.A new graphical method of reactor design for simple or complex reactions is also introduced. This method utilizes continuous stirred tank reactor data directly rather than batch data or kinetics analyses.Reactions are classified according to the kinetic and stoichiometric characteristics which determine the allowable design procedures and the differences in the compostions paths occurring in batch, tubular, or continuous stirred tank reactors.The mathematical analysis of continuous stirred tank reactor systems for complex reactions leads to a set of difference equations. For cases of zero- or first-order reactions these are readily solved as illustrated in examples, even when several independent components influence the reaction kinetics.
    Additional Material: 6 Ill.
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    URL: http://dx.doi.org/10.1002/aic.690050325
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  • 100
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    Transistion from laminar to turbulent flow in pipes (1959)
    Hoboken, NJ : Wiley-Blackwell
    AIChE Journal 5 (1959), S. 433-435 
    Details
    ISSN: 0001-1541
    Keywords: Chemistry ; Chemical Engineering
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In pipeline design, for which one needs a means of ascertaining whether the flow will be laminar or turbulent, the Reynolds number is the criterion for Newtonian fluids. The principal purpose of this study was to formulate a more general criterion to characterize the flow regime and to test this form in application to non-Newtonian fluids.Intuitive physical arguments suggested the use of a local stability parameter which is a function of the ratio of input energy to energy dissipation for an element of fluid. If the parameter is applied to a Newtonian fluid in laminar pipe flow, one finds that it has a maximum value of 0.385 times the critical Reynolds number, or 808. As the criterion is presumed to be general, it is inferred that the value of 808 defines the boundary between stable laminar and stable turbulent pipe flow for all fluids. The inference has been varified for several pseudoplastic fluids.
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/aic.690050407
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