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  • Chemistry  (21,628)
  • Inorganic Chemistry  (6,431)
  • Aircraft Design, Testing and Performance  (107)
  • Aircraft Propulsion and Power  (45)
  • 1955-1959  (13,487)
  • 1935-1939  (8,293)
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Years
Year
  • 1
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    Effects of Nose Radius and Extreme Cooling on Boundary-Layer Transition for Three Smooth 15-Cone-Cylinders in Free Flight at Mach Numbers to 8.50 (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Three highly polished 15- included- angle cone- cylinders with hemispherical tips of several diameters ( 2, 3, and 4 in.) have been flown in order to obtain boundary- layer transition data at very low wall to local stream temperature ratios, and heat- transfer data. All surfaces had a 2-microinch average roughness height. Laminar flow existed over the entire hemispherical nose of the 2- and 3-inch-tip- diameter models throughout the complete flight history. Extreme cooling to wall to local stream temperature ratios at the sonic point as low as 0.20 did not cause transition on the nose for diameters as large as 3 inches. However, extreme cooling did cause early transition on the 4-inch model where it appears probable that transition occurred forward of the 45 station at a wall to local stream temperature ratio of about 0.26. Variations in tip diameter influenced transition downstream of the nose under conditions of extreme cooling. The 2-inch- tip model was laminar at all cone- cylinder stations at temperature ratios as low as 0.32 whereas the 3- and 4-inch-tip models were turbulent at the same local flow conditions but at higher wall to local temperature ratios. Transition on the cone and cylinder of the 3- and 4-inch- tip bodies appeared to be sensitive to local Mach number, and occurred at higher local temperature ratios when values of local Mach number were higher. Increasing the nose diameter from 2 to 3 inches significantly changed the local flow conditions for which laminar flow existed on the cone- cylinder afterbody. However, a further increase in tip size t o a 4-inch diameter had no discernable effect on the local flow conditions at transition. The transition results of the 3- and 4-inch-nose-diameter smooth bodies are similar to those observed on a 7/8-inch-nose-diameter body with roughened surfaces. Turbulent boundary layers resulted in both cases at very low wall to local stream temperature ratios. Both laminar and turbulent heat-transfer data were in good agreement with theoretical Stanton numbers when heat-transfer reduction due to tip blunting was considered.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-3-4-59E , GRC-E-DAA-TN65086
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    NASA TECHNICAL REPORTS
  • 2
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    Lift and Drag of a Swept-Wing Fighter Airplane at Transonic and Supersonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: A flight investigation was made of the lift and drag of a sweptwing fighter airplane in the basic configuration and in a slats-locked-closed configuration over a Mach number range from about 0.63 to about 1.44. At a nominal lift coefficient of 0.1 negligible drag-coefficient difference existed between the two configurations over a comparable Mach number and altitude range. For the basic configuration at zero lift the supersonic drag level was about three times as great as the subsonic drag level, which was about 0.01, whereas the drag-due-to-lift factor increased about 137 percent over the test Mach number range. At comparable Mach numbers the high-altitude data produced a larger lift-curve slope and showed a more pronounced variation of lift-curve slope in the transonic region than did the low-altitude data. For the high-altitude data the lift-curve slope at a Mach number of 1.44 was approximately 62 percent of the value at a Mach number of 0.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-10-1-58H , AFRC-E-DAA-TN47945
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  • 3
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    Wind-tunnel and Piloted Flight Simulator Investigation of a Deflected-slipstream VTOL Airplane, the Ryan VZ-3RY (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-89
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  • 4
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    NASA Research Bearing on Jet Engine Reliability (1959)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Turbojet engine reliability has long been an intense interest to the military users of this type of aircraft propulsion. With the recent inauguration of commercial jet transport this subject has assumed a new dimension of importance. In January l96 the Lewis Research Center of the NASA (then the MACA) published the results of an extensive study on the factors that affect the opera- center dot tional reliability of turbojet engines (ref. 1). At that time the report was classified Confidential. In July l98 this report was declassified. It is thus appropriate at this time to present some of the highlights of the studies described in the NASA report. In no way is it intended to outline the complete contents of the report; rather it is hoped to direct attention to it among those who are center dot directly concerned with this problem. Since the publication of our study over three years ago, the NASA has completed a number of additional investigations that bear significantly on this center dot subject. A second object of this paper, therefore, is to summarize the results of these recent studies and to interpret their significance in relation to turbojet operational reliability.
    Keywords: Aircraft Design, Testing and Performance
    Type: SAE National Aeronautic Meeting; Mar 31, 1959 - Apr 03, 1959; New York, NY; United States
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  • 5
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    Investigation of Low-Subsonic Flight Characteristics of a Model of a Flat-Bottom Hypersonic Boost-Glide Configuration Having a 78 deg Delta Wing (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the low-subsonic stability and control characteristics of a model of a flat-bottom hypersonic boost-glide configuration having 78 deg sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg angle of attack and unstable at angles of attack of about 25 deg and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg angle of attack.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-201 , L-452
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  • 6
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    Analysis of Acceleration, Airspeed, and Gust-Velocity Data From a Four-Engine Transport Airplane Operating Over a Northwestern United States Alaska Route (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Acceleration, airspeed, and altitude data obtained with an NACA VGH recorder from a four-engine commercial transport airplane operating over a northwestern United States-Alaska route were evaluated to determine the magnitude and frequency of occurrence of gust and maneuver accelerations., operating airspeeds, and gust velocities. The results obtained were then compared with the results previously reported in NACA Technical Note 3475 for two similar airplanes operating over transcontinental routes in the United States. No large variations in the gust experience for the three operations were noted. The results indicate that the gust-load experience of the present operation closely approximated that of the central transcontinental route in the United States with which it is compared and showed differences of about 4 to 1 when compared with that of the southern transcontinental route in the United States. In general, accelerations due to gusts occurred much more frequently than those due to operational maneuvers. At a measured normal-acceleration increment of 0.5g, accelerations due to gusts occurred roughly 35 times more frequently than those due to operational maneuvers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-1-17-59L
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  • 7
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    An Analysis of Flight-Test Measurements of the Wing Structural Deformations in Rough Air of a Large Flexible Swept-Wing Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An analysis is made of wing deflection and streamwise twist measurements in rough-air flight of a large flexible swept-wing bomber. Random-process techniques are employed in analyzing the data in order to describe the magnitude and characteristics of the wing deflection and twist responses to rough air. Power spectra and frequency-response functions for the wing deflection and twist responses at several spanwise stations are presented. The frequency-response functions describe direct and absolute response characteristics to turbulence and provide a convenient basis for assessing analytic calculation techniques. The wing deformations in rough air are compared with the expected deformations for quasi-static loadings of the same magnitude, and the amplifications are determined. The results obtained indicate that generally the deflections are amplified by a small amount, while the streamwise twists are amplified by factors of the order of 2.0. The magnitudes of both the deflection velocities and the twist angles are shown to have significant effects on the local angles of attack at the various stations and provide the main source of aerodynamic loading, particularly at frequencies in the vicinity of the first wing-vibration mode.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-3-58L
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  • 8
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    Effect of Cascade Parameters on Rotating Stall (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Analysis of the vortex model proposed by Kriebel, Seidel, and Schwind shows this representation of rotating stall satisfies, at least approximately, the requirements at the cascade. Cascade-parameter-variation effects on rotating stall were studied in a circular cascade and single-stage compressor. Modification of the single-stage compressor stopped the rotating-stall pattern and permitted observation of the pressure and velocity distribution around the annulus. Closer observation might be possible with proper flow-visualization techniques, such as a water pump.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-16-59W
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  • 9
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    Effect of Stator and Rotor Aspect Ratio on Transonic-Turbine Performance (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The effect of stator and rotor aspect ratio on transonic-turbine performance was experimentally investigated. The stator aspect ratios covered were 1.6. 0.8, and 0.4, while the rotor aspect ratios investigated were 1.46 and 0.73. It was found that the observed variation in turbine design-point efficiency was negligible. Thus, within the range of aspect ratio investigated, these results verify for turbines operating in the transonic flow range the finding of a reference report, which showed analytically that, if blade shape and solidity are held constant, the aspect ratio may be varied over a wide range without appreciable change in turbine efficiency.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-2-11-59E , E-177
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  • 10
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    Experimental Evaluation of Cermet Turbine Stator Blades for Use at Elevated Gas Temperatures (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The suitability of cermets for turbine stator blades of a modified turbojet engine was determined at an average turbine-inlet-gas temperature of 2000 F. Such an increase in temperature would yield a premium in thrust from a service engine. Because the cermet blades require no cooling, all the available compressor bleed air could be used to cool a turbine made from conventional ductile alloys. Cermet blades were first run in 100-hour endurance tests at normal gas temperatures in order to evaluate two methods for mounting them. The elevated gas-temperature test was then run using the method of support considered best for high-temperature operation. After 52 hours at 2000 F, one of the group of four cermet blades fractured probably because of end loads resulting from thermal distortion of the spacer band of the nozzle diaphragm. Improved design of a service engine would preclude this cause of premature failure.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-2-13-59E , E-147
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  • 11
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    The Effect of Lower Surface Spoilers on the Transonic Trim Change of a Wind-Tunnel Model of a Fighter Airplane Having a Modified Delta Wing (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter airplane, lower surface spoilers were tested on a 0.055-scale wind-tunnel model. The Mach number range of the tests was 0.8 to 1.2 at Reynolds numbers of approximately 4 million. Although the spoilers produced a moderate decrease in the trim change at low altitudes, they also produced a large increase in drag. Pressure-distribution tests with external fuel tanks showed large pressure changes on the lower surface of the wing due to the tanks.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-27-58A
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  • 12
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    Air-Cooled Turbine Blades with Tip Cap For Improved Leading-Edge Cooling (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation was conducted in a modified turbojet engine to determine the cooling characteristics of the semistrut corrugated air- cooled turbine blade and to compare and evaluate a leading-edge tip cap as a means for improving the leading-edge cooling characteristics of cooled turbine blades. Temperature data were obtained from uncapped air-cooled blades (blade A), cooled blades with the leading-edge tip area capped (blade B), and blades with slanted corrugations in addition to leading-edge tip caps (blade C). All data are for rated engine speed and turbine-inlet temperature (1660 F). A comparison of temperature data from blades A and B showed a leading-edge temperature reduction of about 130 F that could be attributed to the use of tip caps. Even better leading-edge cooling was obtained with blade C. Blade C also operated with the smallest chordwise temperature gradients of the blades tested, but tip-capped blade B operated with the lowest average chordwise temperature. According to a correlation of the experimental data, all three blade types 0 could operate satisfactorily with a turbine-inlet temperature of 2000 F and a coolant flow of 3 percent of engine mass flow or less, with an average chordwise temperature limit of 1400 F. Within the range of coolant flows investigated, however, only blade C could maintain a leading-edge temperature of 1400 F for a turbine-inlet temperature of 2000 F.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-2-9-59E
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  • 13
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    Evaluation of the Levy Method as Applied to Vibrations of a 45 deg Delta Wing (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The Levy method which deals with an idealized structure was used to obtain the natural modes and frequencies of a large-scale built-up 45 deg. delta wing. The results from this approach, both with and without the effects of transverse shear, were compared with the results obtained experimentally and also with those calculated by the Stein-Sanders method. From these comparisons it was concluded that the method as proposed by Levy gives excellent results for thin-skin delta wings, provided that corrections are made for the effect of transverse shear.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-2-59L , L-153
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  • 14
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    An Experimental Investigation of a Triangular Wing of Aspect Ratio 2 and a Body Warped to be Trimmed at M = 2.24 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A cambered and twisted triangular wing of aspect ratio 2 in combination with a cambered body was investigated experimentally to determine the effectiveness of the camber in reducing the drag due to lift at trim at supersonic speeds. Four arrangements were tested comprising all combinations of a symmetrical and a cambered wing with a symmetrical and a cambered body. The camber shape investigated was derived by linearized lifting surface theory for triangular wings with sonic leading edges and satisfied the requirement that the wing be trimmed at the design Mach number and lift coefficient. The experimental results for the cambered wing and cambered body showed that the drag coefficient at trim was always greater, at the same lift coefficient, than that for the untrimmed symmetrical wing and body. The trim lift coefficient was positive and decreased with increasing Mach number. At the design Mach number of 2.24, the trim lift coefficient was somewhat lower and the drag coefficient was higher than values predicted by linearized lifting surface theory for the wing alone. A comparison of the trim lift-drag ratio of the cambered wing and cambered body with values obtained by trimming the symmetrical wing and symmetrical body either with a canard or a trailing-edge flap showed that, at approximately the design Mach number the cambered configuration developed a somewhat higher value than the trailing-edge flap configuration but a lower value than the canard configuration.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-3-59A
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  • 15
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    Flight Behavior of the X-2 Research Airplane to a Mach Number of 3.20 and a Geometric Altitude of 126,200 Feet (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The maximum Mach number and altitude capabilities of the Bell X-2 research airplane were achieved during a program conducted by the U.S. Air Force with Bell Aircraft Corp. providing operational support and the National Aeronautics and Space Administration providing instrumentation and advisory engineering assistance. A maximum geometric altitude of 126,200 feet was attained at a static pressure of 9.4 pounds per square foot and a dynamic pressure of 19.1 pounds per square foot. During the last flight of the airplane, a maximum Mach number of 3.20 was reached. The directionally divergent maneuver which terminated the final high Mach number flight was precipitated by the loss in directional stability that resulted from increasing the angle of attack. The yawing moment from the lateral control was sufficient to initiate the divergence and also to cause,, indirectly, rolling moments that were greater than the aileron capabilities of the airplane. The ensuing violent motions-resulting from inertial roll coupling caused the loss of the aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-137
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  • 16
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    Launch, Low-Speed, and Landing Characteristics Determined from the First Flight of the North American X-15 Research Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The first flight of the North American X-15 research airplane was made on June 8, 1959. This was accomplished after completion of a series of captive flights with the X-15 attached to the B-52 carrier airplane to demonstrate the aerodynamic and systems compatibility of the X-15//B-52 combination and the X-15 subsystem operation. This flight was planned as a glide flight so that the pilot need not be concerned with the propulsion system. Discussions of the launch, low-speed maneuvering, and landing characteristics are presented, and the results are compared with predictions from preflight studies. The launch characteristics were generally satisfactory, and the X-15 vertical tail adequately cleared the B-52 wing cutout. The actual landing pattern and landing characteristics compared favorably with predictions, and the recommended landing technique of lowering the flaps and landing gear at a low altitude appears to be a satisfactory method of landing the X-15 airplane. There was a quantitative correlation between flight-measured and predicted lift-drag-ratio characteristics in the clean configuration and a qualitative correlation in the landing configuration. A longitudinal-controllability problem, which became severe in the landing configuration, was evident throughout the flight and, apparently, was aggravated by the sensitivity of the side-located control stick. In the low-to-moderate angle-of-attack range covered, the longitudinal and directional stability were indicated to be adequate.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-195
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  • 17
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    Subsonic Wing Loadings on a 45 deg Sweptback Wing and Body Combination at High Angles of Attack (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A study has been made of the subsonic pressure distributions and loadings for a 45 deg sweptback-wing and body combination at angles of attack up to 36 deg. The wing had an aspect ratio of 5.5, a taper ratio of 0.53, and NACA 64A010 sections normal to the quarter-chord line and was mounted on a slender body of fineness ratio 12.5. Test results are presented for Mach numbers of 0.30 and 0.50 with corresponding Reynolds numbers of 1.5 and 2.0 million, respectively. The stall patterns and spanwise loadings at high angles of attack for the present model are correlated with those for other 45 deg sweptback wing and body combinations having aspect ratios between 4.0 and 8.0. A tentative approach is presented for extrapolating the Weissinger span-loading method to higher angles of attack, and for deriving the spanwise-load distributions for 45 deg sweptback wings at angles of attack above 20 deg. The investigation also included tests of the body in combination with only one panel of the swept wing. The problem of estimating the normal-force coefficient for the single panel at high angles of attack is considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-1-18-59A
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  • 18
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    Results of a Cyclic Load Test of an RB-47E Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Results of a cyclic load test made by NASA on an EB-47E airplane are given. The test reported on is for one of three B-47 airplanes in a test program set up by the U. S. Air Force to evaluate the effect of wing structural reinforcements on fatigue life. As a result of crack development in the upper fuselage longerons of the other two airplanes in the program, a longeron and fuselage skin modification was incorporated early in the test. Fuselage strain-gage measurements made before and after the longeron modification and wing strain-gage measurements made only after wing reinforcement are summarized. The history of crack development and repair is given in detail. Testing was terminated one sequence short of the planned end of the program with the occurrence of a major crack in the lower right wing skin.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-15-59L , AF-AM-171
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  • 19
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    The Effect of Lift-Drag Ratio and Speed on the Ability to Position a Gliding Aircraft for a Landing on a 5,000-Foot Runway (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Flight tests were made to determine the capability of positioning a gliding airplane for a landing on a 5,000-foot runway with special reference to the gliding flight of a satellite vehicle of fixed configuration upon reentry into the earth's atmosphere. The lift-drag ratio and speed of the airplane in the glides were varied through as large a range as possible. The results showed a marked tendency to undershoot the runway when the lift-drag ratios were below certain values, depending upon the speed in the glide. A straight line dividing the successful approaches from the undershoots could be drawn through a lift-drag ratio of about 3 at 100 knots and through a lift-drag ratio of about 7 at 185 knots. Provision of a drag device would be very beneficial, particularly in reducing the tendency toward undershooting at the higher speeds.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-12-59L , L-406
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  • 20
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    Evaluation of Several Approximate Methods for Calculating the Symmetrical Bending-Moment Response of Flexible Airplanes to Isotropic Atmospheric Turbulence (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Several approximate procedures for calculating the bending-moment response of flexible airplanes to continuous isotropic turbulence are presented and evaluated. The modal methods (the mode-displacement and force-summation methods) and a matrix method (segmented-wing method) are considered. These approximate procedures are applied to a simplified airplane for which an exact solution to the equation of motion can be obtained. The simplified airplane consists of a uniform beam with a concentrated fuselage mass at the center. Airplane motions are limited to vertical rigid-body translation and symmetrical wing bending deflections. Output power spectra of wing bending moments based on the exact transfer-function solutions are used as a basis for the evaluation of the approximate methods. It is shown that the force-summation and the matrix methods give satisfactory accuracy and that the mode-displacement method gives unsatisfactory accuracy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-18-59L , L-143
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  • 21
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    Investigation of a 4.5-Inch-Mean-Diameter Two-Stage Axial-Flow Turbine Suitable for Auxiliary Power Drives (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The design and experimental investigation of a 4.5-inch-mean-diameter two-stage turbine are presented herein and used to study the effect of size on the efficiency of turbines in the auxiliary power drive class. The results of the experimental investigation indicated that design specific work was obtained at design speed at a total-to-static efficiency of 0.639. At design pressure ratio, design static-pressure distribution through the turbine was obtained with an equivalent specific work output of 33.2 Btu per pound and an efficiency of 0.656. It was found that, in the design of turbines in the auxiliary power drive class, Reynolds number plays an important part in the selection of the design efficiency. Comparison with theoretical efficiencies based on a loss coefficient and velocity diagrams are presented. Close agreement was obtained between theory and experiment when the loss coefficient was adjusted for changes in Reynolds number to the -1/5 power.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-4-6-59E
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  • 22
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    Application of Gas Analysis to Combustor Research (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The performance of turbine-engine combustors usually is given in terms of operating limits and combustion efficiency. The latter property is determined most often by measuring the increase in enthalpy across the combustor through the use of thermocouples. This investigation was conducted to determine the ability of gas-analytical techniques to provide additional information about combustor performance. Gas samples were taken at the outlet and two upstream stations and their compositions determined. In addition to over-all combustion efficiency, estimates of local fuel-air ratios, local combustion efficiencies, and heat-release rates can be made. Conclusions can be drawn concerning the causes of combustion inefficiency and may permit corrective design changes to be made more intelligently. The purpose of this investigation was not to present data for a given combustor but rather to show the types and value of additional information that can be gained from gas-analytical data.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-1-26-59E , E-245
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  • 23
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    Flight Tests of A 1/8-Scale Model of the Bell D-188A Jet VTOL Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The Bell D-188A VTOL airplane is a horizontal-attitude VTOL fighter with tilting engine nacelles at the tips of a low-aspect-ratio unswept wing and additional engines in the fuselage. The model could be flown smoothly in hovering and transition flight. In forward flight the model could be flown smoothly at the lower angles of attack but experienced an uncontrollable directional divergence at angles of attack above about 16 deg.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-16-59L , TED-AD-3147 , L-241
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  • 24
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    Comparison of Measured Flapwise Structural Bending Moments on a Teetering Rotor Blade With Results Calculated From the Measured Pressure Distribution (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Flapwise bending moments were calculated for a teetering rotor blade using a reasonably rapid theoretical method in which airloads obtained from wind-tunnel tests were employed. The calculated moments agreed reasonably well with those measured with strain gages under the same test conditions. The range of the tests included one hovering and two forward-flight conditions. The rotor speed for the test was very near blade resonance, and difficult-to-calculate resonance effects apparently were responsible for the largest differences between the calculated and measured harmonic components of blade bending moments. These differences, moreover, were largely nullified when the harmonic components were combined to give a comparison of the calculated and measured blade total- moment time histories. The degree of agreement shown is therefore considered adequate to warrant the use of the theoretical method in establishing and applying methods of prediction of rotor-blade fatigue loads. At the same time, the validity of the experimental methods of obtaining both airload and blade stress measurement is also indicated to be adequate for use in establishing improved methods for prediction of rotor-blade fatigue loads during the design stage. The blade stiffnesses and natural frequencies were measured and found to be in close agreement with calculated values; however, for a condition of blade resonance the use of the experimental stiffness values resulted in better agreement between calculated and measured blade stresses.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-28-59L , L-140
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  • 25
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    Effect of Six Missile-Bay Baffle Configurations and a Rocket End Plate on Ejection Releases of an MB-1 Rocket from a 0.05 Scale Model of the Convair F-106A Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: As a continuation of an investigation of the release characteristics of an MB-1 rocket carried internally by the Convair F-106A airplane, six missile-bay baffle configurations and a rocket end plate have been investigated in the 27- by 27-inch preflight jet of the NASA Wallops Station. The MB-1 rocket used had retractable fins and was ejected from a missile bay modified by the addition of six different baffle configurations. For some tests a rocket end plate was added to the model. Dynamically scaled models (0.04956 scale) were tested at a simulated altitude of 22,450 feet and Mach numbers of 0.86, 1.59, and 1.98, and at a simulated altitude of 29,450 feet and a Mach number of 1.98. The results of this investigation indicate that the missile-bay baffle configurations and the rocket end plate may be used to reduce the positive pitch amplitude of the MB-1 rocket after release. The initial negative pitching velocity applied to the MB-1 rocket might then be reduced in order to maintain a near-level-flight attitude after release. As the fuselage angle of attack is increased, the negative pitch amplitude of the rocket is decreased.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-4-29-59L , AF-AM-57 , L-361
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  • 26
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    Approach and Landing Investigation at Lift-Drag Ratios of 2 to 4 Utilizing a Straight-Wing Fighter Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A series of landings was performed with a straight-wing airplane to evaluate the effect of low lift-drag ratios on approach and landing characteristics. Landings with a peak lift-drag ratio as low as 3 were performed by altering the airplane configuration (extending speed brakes, flaps, and gear and reducing throttle setting). As lift-drag ratio was reduced, it was necessary either to make the landing pattern tighter or to increase initial altitude, or both. At the lowest lift-drag ratio the pilots believed a 270 deg overhead pattern was advisable because of the greater ease afforded in visually positioning the airplane. The values of the pertinent flare parameters increased with the reduction of lift-drag ratio. These parameters included time required for final flare; speed change during final flare; and altitude, glide slope, indicated airspeed, and vertical velocity at initiation of final flare. The pilots believed that the tolerable limit was reached with this airplane in the present configuration, and that if, because of a further reduction in lift-drag ratio, more severe approaches than those experienced in this program were attempted, additional aids would be required to determine the flare-initiation point.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-31
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  • 27
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    Normal Component of Induced Velocity for Entire Field of a Uniformly Loaded Lifting Rotor with Highly Swept Wake as Determined by Electromagnetic Analog (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Values of the normal component of induced velocity throughout the entire field of a uniformly loaded r(rotor at high high speed are presented in the form of charts and tables. Many points were found by an electromagnetic analog, details of which are given. Comparisons of computed and analog values for the induced velocity indicate that the latter are sufficiently accurate for engineering purposes.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TR-R-41
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  • 28
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    Study of Taxiing Problems Associated with Runway Roughness (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This paper briefly summarizes available statistical data on airplane taxi operations, examines the profiles and power spectra of four selected runways and taxiways covering a wide range of surface roughness, considers (on the basis of theoretical and experimental results) the loads resulting from taxiing on such runways over a range of speeds and, by synthesis of the aforementioned results, proposes new criteria for runway and taxiway smoothness which are applicable to new construction and may also be used as a guide for determining when repairs are necessary.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-21-59L
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  • 29
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    Exploratory Investigation of Aerodynamic Flameholders for Afterburner Application (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted to determine the flameholding capabilities of aerodynamic jets at afterburner operating conditions. Stability data for a number of aerodynamic flameholders were obtained in a 5- by 5-inch test section at inlet-air reference velocities up to 600 feet per second, an inlet-air temperature of 1250 F, and a combustor-inlet pressure of 15 inches of mercury absolute. Combustion efficiency and stability data of the more promising combinations were then obtained in a 10- by 12-inch test section at the same test conditions. Both air and stoichiometric mixtures of fuel and air were used in the jets; mixture flow rates were approximately 1 percent by weight of the total air-flow rate. Injection pressures were limited to values that might be available from compressor-bleed air. At a reference velocity of 600 feet per second, aerodynamic flame-holders alone were unable to maintain a stable flame at injection pressures up to 70 pounds per square inches large reductions in velocity were required to achieve flame stabilization. When the aerodynamic jets were used in combination with a V-gutter flameholder with approximately a 30 percent blocked area, flame stabilization was attained at a velocity of 600 feet per second; however, the combustion efficiencies of the various combinations were no greater than that obtained with the V-gutter alone.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-4-9-59E
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  • 30
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    Comparison of Calculated and Experimental Total-Pressure Loss and Airflow Distribution in Tubular Turbojet Combustors with Tapered Liners (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Incompressible-flow calculations were performed to determine the effects of combustor geometric and operating variables on pressure loss and airflow distribution in a tubular combustor with a tapered liner. The calculations include the effects of momentum transfer between annulus and liner gas streams, annulus wall friction, heat release, and discharge coefficients of liner air-entry holes. Generalized curves are presented which show the effects of liner-wall inclination, liner open hole area, and temperature rise across the combustor on pressure loss and airflow distribution for a representative parabolic liner hole distribution. A comparison of the experimental data from 12 tapered liners with the theoretical calculations indicates that reasonable design estimates can be made from the generalized curves. The calculated pressure losses of the tapered liners are compared with those previously reported for tubular liners.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-11-26-58E , E-126
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  • 31
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    Performance of Typical Rear-Stage Axial-Flow Compressor Rotor Blade Row at Three Different Blade Setting Angles (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A comparison of the performance of a single-stage rotor run at three different blade setting angles is presented. The rotor was of a design typical for a last stage of a multistage compressor. At each setting angle, the rotor blade row was operated from 53 to 100 percent of equivalent maximum speed (850 ft/sec tip speed) at constant inlet pressure. Hot-wire anemometry was used to observe rotating-stall and surge patterns in time unsteady flow. Results indicated that an increase in peak pressure ratio and an increase in maximum equivalent weight flow were obtained at each speed investigated when the blade setting angle was decreased. An increase in peak efficiency was achieved with decrease in blade setting angle for part of the range of speeds investigated. However, the peak efficiencies for the three blade setting angles were approximately the same at the maximum speed investigated. The flow ranges for all three configurations were about the same at minimum speed and decreased at almost the same rate when the rotative speed was increased through part of the range of speeds investigated. At maximum speed, the flow range for the smallest setting angle was considerably less than the flow range for the other two configurations. A decrease in efficiency and flow range for the smallest blade setting angle at maximum speed can be attributed primarily to a Mach number effect. In addition, because of the difference in projected axial chord lengths at the casing wall, some effect on performance could be expected from the change in three-dimensional flow occurring at the tip. Rotating-stall characteristics for the two smaller blade setting angles were essentially the same. Only surge could be detected for the largest blade setting angle in the unstable-flow region of operation.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-11-27-58E , E-117
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  • 32
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    Flight Investigation of Effects of Transition, Landing Approaches, Partial-Power Vertical Descents, and Droop-Stop Pounding on the Bending and Torsional Moments Encountered by a Helicopter Rotor Blade (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Flight tests have been conducted with a single-rotor helicopter, one blade of which was equipped at 14 percent and 40 percent of the blade radius with strain gages calibrated to measure moments rather than stresses, to determine the effects of transition, landing approaches, and partial-power vertical descents on the rotor-blade bending and torsional moments. In addition, ground tests were conducted to determine the effects of static droop-stop pounding on the rotor-blade moments. The results indicate that partial-power vertical descents and landing approaches produce rotor-blade moments that are higher than the moments encountered in any other flight condition investigated to date with this equipment. Decelerating through the transition region in level flight was found to result in higher vibratory moments than accelerating through this region. Deliberately induced static droop-stop pounding produced flapwise bending moments at the 14-percent-radius station which were as high as the moments experienced in landing approaches and partial-power vertical descents.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-5-7-59L
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  • 33
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    Application of the Method of Stein and Sanders to the Calculation of Vibration Characteristics of a 45 deg Delta-Wing Specimen (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Generalized influence coefficients are calculated by the method of NACA TN 3640 for a large-scale, built-up, 450 delta-wing specimen. These are used together with appropriate generalized masses to obtain the natural modes and frequencies in symmetric and antisymmetric free-free vibration. The resulting frequencies are compared with those obtained experimentally and are found to be consistently high. Possible sources of the disparities are discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-1-59L
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  • 34
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    Some Static Oscillatory and Free Body Tests of Blunt Bodies at Low Subsonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Some blunt-body shapes considered suitable for entry into the earth's atmosphere were tested by both static and oscillatory methods in the Langley stability tunnel. In addition, free-fall tests of some similar models were made in the Langley 20-foot free-spinning tunnel. The results of the tests show that increasing the flare of the body shape increased the dynamic stability and that for flat-faced shapes increasing the corner radius increased the stability. The test data from the Langley stability tunnel were used to compute the damping factor for the models tested in the langley 20-foot free-spinning tunnel. For these cases in which the damping factor was low, -1/2 or less, the stability was critical and sensitive to disturbance. When the damping factor was about -2, damping was generally obtained.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-22-59L , L-157
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  • 35
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    Investigation of the Effects of Low Reynolds Number Operation on the Performance of a Single-Stage Turbine with a Downstream Stator (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: High-altitude turbojet performance is adversely affected by the effects of low air density. This performance loss is evaluated as a Reynolds number effect, which represents the increased significance of high fluid viscous forces in relation to dynamic fluid forces as the Reynolds number is decreased. An analytical and experimental investigation of the effects of low Reynolds number operation on a single-stage, high-work-output turbine with a downstream stator was carried out at Reynolds numbers of 182,500, 39,600, and 23,000, based on average rotor-design flow conditions. At low Reynolds numbers and turbulent flow conditions, increased viscous losses caused decreased effective flow area, and thus decreased weight flow, torque, and over-all efficiency at a given equivalent speed and pressure ratio. Decreasing the Reynolds number from 182,500 to 23,000 at design equivalent speed resulted in a 5.00-point loss in peak over-all turbine efficiency for both theory and experiment. The choking equivalent weight flow decreased 2.30 percent for these conditions. Limiting loading work output was reached at design equivalent speed for all three Reynolds numbers. The value of limiting loading work output at design speed decreased 4.00 percent as Reynolds number was decreased from 182,500 to 23,000. A theoretical performance-prediction method using basic boundary-layer relations gave good agreement with experimental results over most of the performance range at a given Reynolds number if the experimental and analytical design operating conditions were carefully matched at the highest Reynolds number with regard to design performance parameters. High viscous losses in the inlet stator and rotor prevented the attainment of design equivalent work output at the lowest Reynolds number of 23,000.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-9
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  • 36
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    A Limited Study of a Hypothetical Winged Anti-ICBM Point-Defense Missile (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A preliminary investigation was conducted to determine whether a warhead stage of an antimissile missile could be placed within an arbitrary 2-nautical-mile-radius maneuver cylinder around an intercontinental-ballistic-missile (ICBM) flight path above an altitude of 140,000 feet, a horizontal range of 40 nautical miles, at a flight-path angle of approximately 20 deg, and within 50 seconds after take-off using only aerodynamic forces to turn the antimissile missile. The preliminary investigation indicated that an antimissile missile using aerodynamic forces for turning was capable of intercepting the ICBM for the stated conditions of this study although the turning must be completed below an altitude of approximately 70,000 feet to insure that the antimissile missile will be at the desired flight-path angle. Trim lift coefficients on the order of 2 to 3 and a maximum normal-acceleration force of from 25g to 35g were necessary to place the warhead stage in intercept position. The preliminary investigation indicated that for the two boosters investigated the booster having a burning time of 10 seconds gave greater range up the ICBM flight path than did the booster having a burning time of 15 seconds for the same trim lift coefficient and required the least trim lift coefficient for the same range.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-14-59L
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  • 37
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    Roll Utilization of an F-100A Airplane During Service Operational Flying (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: As a means of evaluating the roll utilization of a fighter airplane capable of supersonic speeds, an instrumented North American F-100A fighter airplane was flown by U.S. Air Force pilots at Nellis Air Force Base, NV, during 20 hours of service operational flying. Mach numbers up to 1.22 and altitudes up to 50,000 feet were realized in this investigation. Results of the study showed that except for high g barrel rolls performed as evasive maneuvers and rolls performed in acrobatic flying, rolling was utilized primarily as a means of changing heading. Acrobatic and air combat maneuvering produced the largest bank angles (1,200 deg), roll velocities (3.3 radians/sec), rolling accelerations (8 radians/sq sec) and sideslip angles (10.8 deg). Full aileron deflections were utilized on numerous occasions. Although high rolling velocities and accelerations also were experienced during several air-to-air gunnery missions, generally, air-to-air gunnery and air-to-ground gunnery and bombing required only two-thirds of maximum aileron deflection. The air-to-air gunnery and air combat maneuvers initiated from supersonic speeds utilized up to two-thirds aileron deflection and bank angles of less than 18 deg and resulted in rolling velocities and accelerations of 2 radians per second and 4.6 radians/sq sec, respectively. Rolling maneuvers were often initiated from high levels of normal acceleration, but from levels of negative normal acceleration only once.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-1-58H
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  • 38
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    Flight Measurements of the Effect of a Controllable Thrust Reverser on the Flight Characteristics of a Single-Engine Jet Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A flight investigation was undertaken to determine the effect of a fully controllable thrust reverser on the flight characteristics of a single-engine jet airplane. Tests were made using a cylindrical target-type reverser actuated by a hydraulic cylinder through a "beep-type" cockpit control mounted at the base of the throttle. The thrust reverser was evaluated as an in-flight decelerating device, as a flight path control and airspeed control in landing approach, and as a braking device during the ground roll. Full deflection of the reverser for one reverser configuration resulted in a reverse thrust ratio of as much as 85 percent, which at maximum engine power corresponded to a reversed thrust of 5100 pounds. Use of the reverser in landing approach made possible a wide selection of approach angles, a large reduction in approach speed at steep approach angles, improved control of flight path angle, and more accuracy in hitting a given touchdown point. The use of the reverser as a speed brake at lower airspeeds was compromised by a longitudinal trim change. At the lower airspeeds and higher engine powers there was insufficient elevator power to overcome the nose-down trim change at full reverser deflection.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-4-26-59A , A-135
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  • 39
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    Engine Operating Conditions that Cause Thermal-Fatigue Cracks in Turbojet-Engine Buckets (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Five engine tests were conducted to definitely establish the failure mechanism of leading-edge cracking and to determine which conditions of engine operation cause the failures. Five groups of S-616 and M-252 buckets from master lots were run consecutively in the same J47-25 engine. The tests included a steady-state run at full-power conditions, rapid cycling between idle and rated speed, and three different start-stop tests. The first start-stop test consisted of cycles of start and stop with 5 minutes of idle speed before each stop; the second included cycles of start and stop but with 15 minutes of rated speed before each stop; the third consisted of cycles of gradual starts and normal stops with 5 minutes at idle speed before each stop. The test results demonstrated that the primary cause of leading-edge cracking was thermal fatigue produced by repeated engine starts. The leading edge of the bucket experiences plastic flow in compression during starts and consequently is subjected to a tensile stress when the remainder of the bucket becomes heated and expands. Crack initiation was accelerated when rated-speed operation was added to each normal start-stop cycle. This acceleration of crack formation was attributed to localized creep damage and perhaps to embrittlement resulting from overaging. It was demonstrated that leading-edge cracking can be prevented simply by starting the engine gradually.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-MEMO-4-7-59E , E-281
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  • 40
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    Experimental Investigation of a 0.35 Hub-Tip Radius Ratio Transonic Axial Flow Rotor Designed for 40 Pounds per Second per Square Foot with a Design Tip Diffusion Factor of 0.20 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: In order to determine the effect of a low design diffusion factor on the performance of a transonic axial-flow compressor rotor, a high-specific-flow rotor with a 0.35 hub-tip radius ratio was designed, fabricated and tested. This rotor used a design tip diffusion factor of 0.20 with a design corrected specific weight flow of 40 pounds per second per square foot of frontal area, a total-pressure ratio of 1.27, and an adiabatic efficiency of 0.96. The design, rotor performance, and blade element performance are presented with a discussion on rotor shock losses and a comparison with a similarly designed rotor with a tip diffusion factor of 0.35. At the design corrected tip speed of 1100 feet per second, a peak rotor adiabatic efficiency of 0.88 was attained at a corrected specific weight flow of 39 pounds per second per square foot of frontal area with a mass-averaged total-pressure ratio of 1.27. The blade element tip diffusion factor was 0.281, which is 0.08 higher than the design value of 0.20. Peak efficiencies of 0.95, 0.91, 0.89, and 0.85 were obtained at 70, 80, 90, and 110 percent of design speed, respectively. Comparison of the performance of the rotor reported herein and a similarly designed rotor with increased blade loading indicates that higher blade loading results in a more desirable rotor because of a higher pressure ratio and equivalent efficiency. Computed values of shock losses at the rotor tip section indicate that the losses at peak efficiency are primarily a function of shock losses since the profile losses are only a small percentage of the total loss.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-86
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  • 41
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    Measurements Obtained During the First Landing of the North American X-15 Research Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The first landing of the X-15 airplane was made at 8:43 a.m., June 8, 1959, on the hard surface of Rogers Dry Lake. One purpose of the first-glide flight was to evaluate the effectiveness of the landing-gear system. Some results are presented of the landing-approach characteristics, the impact period, and the runout phase of the landing maneuver. The results indicate that the touchdown was accomplished at a vertical velocity of 2.0 feet per second for the main gear and 13.5 feet per second for the nose gear. These vertical velocities were within the values of sinking speeds established by structural design limitations. However, permanent structural deformation occurred in the main-landing-gear system as a result of the landing, and a reevaluation of the gear is being made by the manufacturer. The landing occurred at a true ground speed of 158 knots for main-gear touchdown at an angle of attack of 8.50. The incremental acceleration at the main gear was 2.7g and 7.39 at the nose gear as a result of the landing. The incremental acceleration at the center of gravity of the airplane was 0.6g for the main-gear impact and 2.4g for the nose-gear impact. The incremental acceleration at the main gear as a result of the nose-gear impact was 4.8g. The extreme rearward location of the main-gear skids appears to offer satisfactory directional stability characteristics during the run- out phase of the landing. No evidence of nosewheel shimmy was indicated during the impact and runout phase of the landing despite the absence of a shimmy damper on the nose gear. The maximum amount of skid wear as a result of the landing was on the order of 0.005 inch. No appreciable amount of tire wear was indicated for the dual, corotating nosewheels.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-207
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  • 42
    Electronic Resource
    Electronic Resource
    Über Silikone, XLIV. Umsetzung von Tetrachlorkohlenstoff mit Silicium (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1018-1027 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei nochmaliger Untersuchung der Umsetzung von CCl4 mit Si/Cu-Gemischen werden, wie bereits bekannt, SiCl4, C2Cl4 und Si2Cl6 gefunden. Darüber hinaus lief eine direkte Synthese. Sie führte wahrscheinlich zur Bildung des allerdings dabei nicht nachgewiesenen Cl3C·SiCl3. Dagegen wurde die nach der direkten Synthese entstandene Verbindung C(SiCl3)4 erstmalig aufgefunden.  -  Die Entstehung der ebenfalls nachgewiesenen Verbindungen Cl3SiC·C⋮CC·SiCl3 und Cl3SiC·(Cl)C:C(Cl)C·SiCl3 wird durch Dechlorierungen des Cl3CC·SiCl3 mit Kupfer erklärt.  -  Für die neuen Verbindungen wurden Strukturbeweise geführt. Es wurden C2Cl4 und Cl3CC·SiCl3 mit Si/Cu-Gemischen umgesetzt. Die letzte Umsetzung ergab dieselben Reaktionsprodukte wie das CCl4, so daß auch bei diesem eine direkte Synthese über das Cl3CC·SiCl3 glaubhaft gemacht ist.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920504
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  • 43
    Electronic Resource
    Electronic Resource
    Zur Struktur von Organoschwefelverbindungen, II. Eigenschaften von Thionitriten (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1048-1055 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Eigenschaften von tert.-Butylthionitrit, Triphenylmethylthionitrit und tert.-Butylthionitrat werden Rückschlüsse auf die Elektronenstruktur der schwefelhaltigen Gruppe gezogen.
    Additional Material: 2 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920507
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  • 44
    Electronic Resource
    Electronic Resource
    Über die säurekatalysierte Aldolreaktion des Formaldehyds mit Aceton. Zur Kenntnis der Anhydro-ennea-heptose. Die Synthese der Bisanhydro-ennea-heptose (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1072-1081 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Als weiteres Beispiel für die präparative Überlegenheit der säurekatalysierten Aldolreaktionen des Formaldehyds gegenüber den OH⊖-katalysierten wird über die Synthese der bisher unbekannten Bisanhydro-ennea-heptose, die das Ringsystem des 3.7-Dioxa-bicyclo-[1.3.3]-nonans enthält, berichtet.  -  Bei der Untersuchung des Verhaltens der Bisanhydro-ennea-heptose gegen Alkalien machten sich in der Abspaltbarkeit der Hydroxymethylgruppen charakteristische Unterschiede geltend, deren Erklärung in den konstitutionell-konstellativen Gegebenheiten zu suchen ist.  -  Bei dem Versuch einer Ringerweiterung an der Anhydro-ennea-heptose mit Diazomethan bildet sich eine Verbindung C9H16O5, die wahrscheinlich kein Derivat des Oxa-cycloheptanons-(4), sondern ein Derivat des Tetrahydro-γ-pyrons ist.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920510
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    1-Veratryl-isochinolin-Derivate (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1092-1101 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Substituierte Ammoniumsalze vom Typ I liefern mit Abkömmlingen des Phenylglyoxals in Methanol in glatter Reaktion Lactolid-Basen vom Typ II. Aus diesen lassen sich verschiedene Octa- bzw. Decahydroisochinolin-Derivate darstellen, die in 1-Stellung einen substituierten Benzylrest tragen.
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  • 46
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    Autoxydation von Kohlenwasserstoffen, XXIII. Zur jodometrischen Bestimmung organischer Hydroperoxyde (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1115-1117 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die jodometrische Bestimmung der Hydroperoxyde von Benzolkohlenwasserstoffen kann durch katalytische Wirkung von Kupferionen verbessert werden.
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    Eine vereinfachte Oligosaccharid-Synthese (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1135-1139 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Umsetzung von Tetraacetyl-α-D-glucopyranosylbromid und Tetraacetyl-6-trityl-β-D-glucopyranose mit Silberperchlorat oder Silberfluoroborat in Nitromethan liefert in guter Ausbeute Octaacetyl-β-gentiobiose. Die gleiche Umsetzung mit einem Überschuß an Tetraacetyl-α-D-glucopyranosylbromid und Silberperchlorat führt zur Octaacetyl-α-gentiobiose. Es wird eine Deutung des Reaktionsablaufs gegeben.
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    URL: http://dx.doi.org/10.1002/cber.19590920521
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    Studien in der Vitamin D-Reihe, XXVIII. Photo-Isomerisierung des Tachysterins2 zum Präcalciferol (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1126-1129 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Tachysterin2 wurde mit durch Glas gefiltertem Quecksilberdampflicht in Präcalciferol2 umgewandelt.
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    URL: http://dx.doi.org/10.1002/cber.19590920519
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    Radiochemische Untersuchungen über die Mercurierung von Ammonium-Ionen in wäßrigen Lösungen mit 203Hg (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1152-1158 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Um eine Aussage über den Reaktionsmechanismus bei der Mercurierung des Ammonium-Ions in wäßrigen Lösungen machen zu können, wurde Quecksilber-(II)-diamminchlorid, Hg(NH3)2Cl2, mit wäßriger Ammoniumacetat-Lösung zum sog. „unschmelzbaren Präzipitat“, HgNH2Cl, umgesetzt. Die Lösung enthielt 1 Mol. 203Hg(CH3CO2)2 pro Mol. des Diammoniakates.Die beiden heterogenen Austauschreaktionen Hg(NH3)2Cl2/[203Hg(NH3)4]2⊕ und HgNH2Cl/[203Hg(NH3)4]2⊕ wurden in Abhängigkeit von der Temperatur untersucht.
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    Isomere Decalindiole-(1.4) (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1158-1163 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Von den sechs möglichen Isomeren des Decalindiols-(1.4) wurden zwei der Reihe des cis-Decalins und zwei der Reihe des trans-Decalins angehörende Diole durch Reduktion von cis- und trans-Decalindion-(1.4) sowie durch katalyt. Hydrierung von Naphthohydrochinon-(1.4) und ar-Tetralindiol-(5.8) mit Raney-Nickel im Autoklaven erhalten, eindeutig der cis- und trans-Reihe zugeordnet und durch Derivate charakterisiert.
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    Eine neue Methode zur Darstellung langkettiger Carbonsäuren, XVI. Über die Japp-Klingemann-Reaktion bei monoalkylierten Dihydroresorcinen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1184-1188 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Einwirkung von Aryldiazoniumsalzen auf verschiedene monoalkylierte Dihydroresorcine wurde untersucht. Dabei wurden im glatten Reaktionsverlauf δ-Keto-δ-arylhydrazono-carbonsäuren erhalten. Die gleiche Reaktion führte beim 2-Acetamino-dihydroresorcin infolge einer sekundär verlaufenden Wasserabspaltung zu einem Derivat des 1.2.4-Triazols, dessen Konstitution bewiesen wurde.
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    Stickstoffhaltige Peroxyde, I. Aminoalkylierung von Alkylhydroperoxyden (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1206-1212 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Umsetzung von Alkylhydroperoxyden oder Wasserstoffperoxyd mit Formaldehyd und sekundären Aminen werden nach Art der Mannich-Reaktion Aminoalkylperoxyde erhalten. In mineralsaurer Lösung gelingt auch die Umsetzung von Benzamid oder Harnstoff mit Formaldehyd und Alkylhydroperoxyden.
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    Über bi- und polycyclische Azulene, XXXIX. Carboxychlorierung von Azulenen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1216-1223 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Einführung der Carbonsäurechloridgruppe in 1- bzw. 3-Stellung des Azulensystems gelingt durch Substitution mittels Phosgens ohne Friedel-Crafts-Katalysatoren. Befindet sich in Nachbarstellung zur Carbonsäurechloridgruppe am 7-Ring kein Substituent, so lassen sich die Verbindungen zu den freien Carbonsäuren hydrolysieren, andernfalls tritt Decarboxylierung ein. Die Säurechloride lassen sich in Ester, Amide und Anilide überführen. Die spektralen Verschiebungen gegenüber den zugrunde liegenden Azulenen werden diskutiert.
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    Verbindungen der Hexahydro-adrenalin-Reihe (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1195-1205 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Hydrierung des Adrenalins mit Raney-Nickel liefert keine brauchbaren Ergebnisse. Das Hexahydro-adrenalin (Xb) wird deshalb synthetisch aus Tetrahydro-benzaldehyd in 5 Stufen in guter Ausbeute dargestellt. Es wird gezeigt, daß das synthetische Produkt eine sterisch weitgehend einheitliche Verbindung ist und die 3(trans).4(cis)-Konfiguration besitzt.
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    Stickstoffhaltige Peroxyde, II. Peroxyde aus Enaminen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1212-1215 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus cyclischen Ketonen und sekundären Aminen erhältliche α.β-ungesättigte Amine addieren Wasserstoffperoxyd an der Doppelbindung und geben kristalline Peroxyde.
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    Berichtigung (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1237-1237 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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    URL: http://dx.doi.org/10.1002/cber.19590920537
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    Einige Umsetzungen des Tetrahydroxy-p-benzochinons (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1239-1246 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Tetrahydroxy-p-benzochinon zeigt einige Eigenschaften, die es als „doppeltes aci-Redukton“ erscheinen lassen. So erleidet es „Diazo-Spaltung“ unter Bildung von Mesoxalsäure-bis-arylhydrazid. Diazomethan verwandelt es in den Tetramethyläther, der leicht, sogar durch den Ausgangsstoff, zum entspr. Hydrochinon reduziert wird. Es werden noch Acetyl- und Aminoderivate des Tetrahydroxy-p-benzochinons und seines Dimethyläthers beschrieben sowie die UV- und IR-Spektren diskutiert.
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    Synthese weiterer Oligopeptide aus L-Glutaminsäure und Glycin sowie L-Tyrosin (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1276-1287 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Ausgehend von den in der ersten Veröffentlichung(1) beschriebenen Substanzen wurden Derivate der folgenden Peptide synthetisiert: Glycyl-L-glutaminsäure, Glycyl-glycyl-L-glutaminsäure, γ-L-Glutamyl-glycin, α- und γ-L-Glutamylglycyl-L-glutaminsäure, α- und γ-L-Glutamyl-α-L-glutamyl-glycin und α-L-Glutamyl-L-tyrosin. Auch einige freie Peptide konnten erhalten werden. Als interessante Nebenprodukte der Peptidsynthese über gemischte Anhydride mit Kohlensäure-halbestern wurden in zwei Fällen Diacylimide erhalten.
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    Überführung von D-Glucosamin in Oxazolon- und OxazolinderivateVorliegende Arbeit wurde mit Hilfsmitteln ausgeführt, die die Rockefeller Foundation in dankenswerter Weise meinem Laboratorium zur Verfügung stellte. L. Zervas. (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1288-1293 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Beim Behandeln von N-Benzoyl-D-glucosamin (IV) mit chlorwasserstoffhaltigem Aceton entsteht das Acetonderivat VII eines Phenyloxazolins, welches Furanosestruktur besitzt. Dieses wird mit chlorwasserstoffhaltigem Methanol in das entsprechende Aceton-β-methylfuranosid IX und anschließend in das acetonfreie β-Methylfuranosid X umgewandelt.  -  Behandeln von O-Tetraacetyl-N-carbobenzoxy-D-glucosamin (XI) mit TiCl4 oder mit AlCl3/PCl5 führt unter Abspaltung von Benzylchlorid zur Bildung eines Oxazolonderivates (XIII).
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    Derivate der Zucker-mercaptale, XVI. Methylphenylhydrazone und Phenylosazone der Monobenzoyl-aldosen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1313-1319 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Methylphenylhydrazone der Monobenzoyl-aldosen liegen im kristallisierten und gelösten Zustand nur als Schiffsche Basen vor, sie zeigen keine Mutarotation und lassen sich zu 5-Benzoyl-2.3.4-triacetyl-pentose- bzw. 6-Benzoyl-2.3.4.5-tetraacetyl-hexose-methylphenylhydrazonen acetylieren, deren Struktur durch Synthese bewiesen wird. Die aus Monobenzoyl-aldose-phenylhydrazonen mit Phenylhydrazin darstellbaren Monobenzoyl-aldose-phenylhydrazonen werden sehr leicht zu Aldose-phenylosazonen und Benzoesäure hydrolysiert.
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    Über substituierte Pivalophenone (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1329-1335 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Darstellung des Monobrom-, Monojod- und Trimethoxy-pivalophenons werden beschrieben. Die Halogenverbindungen erleiden bei der Einwirkung wäßriger Alkalien eine hydrolytische Spaltung. Die Methoxyverbindung ist gegen Alkalien stabil.
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    Über die Anlagerung von Pyrrol, 1- und 2-Methyl-pyrrol an β-Aroyl-acrylsäuren (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1363-1366 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: β-Aroyl-acrylsäuren reagieren mit Pyrrol, 1- und 2-Methyl-pyrrol nach dem Schema der substituierenden Addition.
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    Zur Chemie der p-Chinole, I. Darstellung des 17β-Hydroxy-östra-p-chinols und seiner Acetate (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1386-1397 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Oxydation von Tetralol-(6) und Östradiol-17-monoacetat mit Bleitetraacetat werden Tetralin-p-chinolacetat und 17β-Acetoxy-östra-p-chinol-(10ζ)-acetat dargestellt. Aus den Chinolacetaten lassen sich die Chinole durch basenkatalysierte Umesterung in Freiheit setzen. Dem aufgezeigten Weg kommt allgemeine Bedeutung zur Darstellung von p-Chinolen zu.
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    Synthetische Arbeiten in der Reihe der aromatischen Erythrina-Alkaloide, II. Eine neue Vorstufe zum Aufbau von Erythrinanen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1472-1477 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: β-Phenyl-äthylamine lassen sich mit Cyclohexanon-(2)-essigsäure zu partiell hydrierten Oxindol-Derivaten kondensieren, die durch Ringschluß in Verbindungen der Erythrinan-Reihe übergeführt werden.
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    Notiz zur Acylierung von Hydrazin mit Chlorameisensäure-benzylester (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1478-1480 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Umsetzung von Chlorameisensäure-benzylester mit überschüssigem Hydrazinhydrat in absol. Chloroform ergibt Carbobenzoxy-hydrazin. In wäßrigem Medium entsteht vorwiegend N.N′-Dicarbobenzoxy-hydrazin (I), das von rauchender Salpetersäure leicht zu Azodicarbonsäure-dibenzylester (II) dehydriert wird.
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    Über Kumulene, X.IX. Mitteil.: R. Kuhn und H. Fischer, Angew. Chem. 70, 705 [1958].cis-trans-Isomerie bei Dinitro-tetraphenyl-kumulenenTeil der Dissertat. D. Blum, Univ. Heidelberg 1957. (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1483-1500 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wurden 2 Tetraphenyl-äthylene, 2 Tetraphenyl-butatriene und 2 Tetraphenyl-hexapentaene mit je 2 meta- bzw. para-ständigen Nitrogruppen dargestellt. Es gelang, die beiden Äthylene durch Kristallisation und das Butatrien mit m-ständigen NO2-Gruppen durch Chromatographie in der cis- und in der trans-Form zu gewinnen. Damit ist bei einem zweiten Beispiel die von J. H. van't Hoff 1874 vorausgesagte Isomerie an einer Verbindung verwirklicht worden, in der 4 C-Atome durch 3 Doppelbindungen verknüpft sind.  -  Die Isomeren des Triens sind lichtempfindlich. Das Mengenverhältnis cis : trans im photochemischen Gleichgewicht entspricht der Zusammensetzung des Kumulens, wie es bei der Synthese anfällt. Die thermische cis-trans-Umlagerung der Butatriene läßt sich vorzüglich IR-spektroskopisch verfolgen. Die Zuordnung der mit A und B bezeichneten isomeren Butatriene zur cis- und trans-Formel wird diskutiert.  -  Von den beiden Hexapentaenen konnte dasjenige mit 2 p-ständigen Nitrogruppen in roten Kristallen, aber nicht in cis-trans-isomeren Formen gewonnen werden. Das entsprechende Hexapentaen mit 2 m-ständigen NO2-Gruppen war in Lösung beständig, es zersetzte sich aber teilweise bei Entfernung des Lösungsmittels.
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    Über eine Umsetzung von 1.3.5-Trinitro-benzol mit Phloroglucin in alkalischer Lösung, II (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1517-1523 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Umsetzung von 1.3.5-Trinitro-benzol mit Nitrophloroglucin sowie diejenige von Pikrinsäure mit Phloroglucin führt zu polycyclischen Verbindungen. Deren adamantanartige Konstitution wird auf Grund UV-spektroskopischer Vergleiche diskutiert.
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    Synthesen mit Dicarbonsäuren, XXVI. Dialdehyde aus Dibrom-dicarbonsäuren nach Curtius (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1559-1563 
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    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: α.α′-Alkandialdehyde wurden durch Abbau von α.α′-Dibrom-dicarbonsäuren nach Curtius erhalten. Aus α.α′-Dibrom-korksäure bzw. α.α′-Dibrom-azelainsäure entstanden unter geeigneten Bedingungen l-Formyl-cyclopenten-(1) bzw.-cyclohexen-(1).
    Type of Medium: Electronic Resource
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    Säureempfindliche Isochinolin-Derivate durch Ringschluß (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1573-1578 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Der durch Säuren katalysierte Isochinolin-Ringschluß ist unter bestimmten Bedingungen auch mit Substanzen durchführbar, die eine säureempfindliche Gruppe enthalten. Auf diese Weise lassen sich Enoläther bzw. Acetale des Decahydroisochinolons herstellen (XII bzw. XIII), die durch nachfolgende Hydrolyse das freie α.β-ungesättigte Ringketon (XVI) liefern, das man durch direkten Ringschluß nicht erhalten kann.
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    URL: http://dx.doi.org/10.1002/cber.19590920713
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    Die Anlagerung von Ammoniak an Δ1-Tetrahydrobenzoesäure und Cyclopenten-(1)-carbonsäure-(1) und die eindeutige sterische Zuordnung der entstehenden β-Aminosäuren (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1594-1599 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei der Anlagerung von Ammoniak an Δ1-Tetrahydrobenzoesäure und Cyclopenten-(1)-carbonsäure-(1) entstehen ausschließlich die trans-β-Aminosäuren. Der Nachweis der Konfiguration erfolgt bei den entsprechenden cis-Aminosäuren, die durch Hofmannschen Abbau der cis-Hexahydrophthalamidsäure (V) und des cis-Cyclopentan-dicarbonsäure-(1.2)-monoamids erhalten werden. cis-und trans-2-Amino-cyclopentan-carbonsäure-(1) wurden erstmals dargestellt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920716
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    Derivate der Zucker-mercaptale, XVII. Die partielle Veresterung von D-Arabinose-mercaptalen mit Sulfonsäurechloriden und eine einfache Synthese der 5-Desoxy-D-arabinose (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1618-1623 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: D-Arabinose-mercaptale lassen sich mit p-Toluolsulfonsäure- und mit Methansulfonsäurechlorid in Pyridin bei tiefer Temperatur partiell zu 5-Tosyl- bzw. 5-Mesyl-D-arabinose-mercaptalen verestern. Diese werden mit Lithiumaluminiumhydrid zu 5-Desoxy-D-arabinose-mercaptalen reduziert. Daraus gewinnt man durch Abspalten von Mercaptan die 5-Desoxy-D-arabinose.
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    URL: http://dx.doi.org/10.1002/cber.19590920720
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  • 72
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    Heterocyclische Verbindungen, VI. Chinoxalinsynthesen mit Dehydro-L-ascorbinsäure (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1550-1558 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die gleichzeitige Einwirkung von o-Phenylendiamin und Phenylhydrazin auf Dehydro-L-ascorbinsäure führt zum 2-Hydroxy-3-[1′-phenylhydrazono-L-threo-2′.3′4′-trihydroxy-butyl]-2.2′-anhydro-chinoxalin, dessen Natriumsalz beim Erhitzen in Wasser unter Ausbildung eines anellierten Pyrazolringes zum 1-Phenyl-3-[L-threo-trihydroxy-propyl]-flavazol kondensiert. Dagegen entsteht unter dem Einfluß von Hydroxylamin-hydrochlorid das 2-Hydroxy-3-[1′-phenyl-5′-hydroxymethyl-pyrazolyl-(3′)]-chinoxalin. Zu der gleichen Verbindung gelangt man auch durch alkalische Verseifung der Diacetylverbindung des Ausgangsstoffes.
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    URL: http://dx.doi.org/10.1002/cber.19590920710
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  • 73
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    Synthese von 3-Oxo-piperidin-Derivaten (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1579-1586 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es wird der Nachweis erbracht, daß bei der Dieckmann-Kondensation des Esters IVc vorwiegend der Ketoester I entsteht. Hydrierung und Hydrolyse führt zu 3-Hydroxy-piperidin-carbonsäure-(2). Ozonspaltung und Hydrolyse ergibt Oxalsäure. Eine entsprechende Kondensation, ausgehend vom Ester IXc, ergibt den ungesättigten Piperidonester X.
    Additional Material: 1 Ill.
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  • 74
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    Die Anlagerung von Ammoniak an Shikimisäure (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1587-1593 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei der Anlagerung von Ammoniak an Shikimisäure (I) entstehen vorwiegend zwei stereoisomere Aminosäuren der Konstitution III und IV.
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    URL: http://dx.doi.org/10.1002/cber.19590920715
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  • 75
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    Oxydationsstudien an einigen Amino-mercaptanen (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1679-1694 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: o-Substituierte Benzole mit 1. aliphatischer Amino- und aromatischer Mercaptogruppe und 2. aliphatischer Mercapto- und aromatischer Aminogruppe wurden in wäßrig-alkoholischem Medium oxydiert. In der 1. Kategorie resultierten je nach pH Sulfenamid oder Disulfid; im geeigneten Fall trat weitere Dehydrierung zum 1.2-Benzisothiazol-Derivat ein. Es wurde ein pH-abhängiges Gleichgewicht Disulfid ⇌ Sulfenamid + Aminomercaptan festgestellt. In der 2. Kategorie lief die Bildung des Sulfenamids (2.1-Benzisothiazol) und des Disulfids nebeneinander in pH-abhängigen Mengenverhältnissen. Ein übergang Disulfid → Sulfenamid konnte nur unter bestimmten oxydativen Bedingungen erzielt werden. Es wurde an diesem Beispiel gezeigt, daß auch unter günstigen sterischen Verhältnissen die aromatische Aminogruppe nicht in der Lage ist, die aliphatische Disulfid-Gruppe zu spalten.
    Additional Material: 2 Tab.
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    Hydantoine, Thiohydantoine, Glykocyamidine, IV. Notiz über die Orientierung bei der Monomethylierung des 5.5-Diphenyl-glykocyamidins (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1710-1711 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 5.5-Diphenyl-glykocyamidin wird durch Methyljodid in 3-Stellung methyliert. Durch Ammonolyse (bzw. Aminolyse) von 1-Methyl-2-methylmercapto-4.4-diphenyl-imidazolon-(5) in Gegenwart von Ammoniumsalzen wurden weitere-3-substituierte Glykocyamidine dargestellt.
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    URL: http://dx.doi.org/10.1002/cber.19590920736
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    Masthead (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959) 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920801
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  • 78
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    Über Trimethylsilylderivate von Uronsäuren (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1638-1643 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Umsetzungen von Glucuron- und Galakturonsäure und einigen ihrer Derivate mit Trimethylchlorsilan werden Substanzen erhalten, die i. Vak. gut destillieren und aus denen sich die Ausgangsverbindungen durch Alkoholyse leicht zurückgewinnen lassen. Die Eigenschaften der Trimethylsilylverbindungen werden beschrieben.
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    URL: http://dx.doi.org/10.1002/cber.19590920724
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    Synthese von (±)-Corypalmin und (±)-Isocorypalmin (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1654-1657 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: (±)-Corypalmin und (±)-Isocorypalmin wurden nach einer vereinfachten Methode zur Darstellung von Tetrahydro-protoberberinen synthetisiert.
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/cber.19590920726
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  • 80
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    Über Oxoniumsalze in der Reihe der Carbonsäuren und der Kohlensäure (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1828-1834 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Carbonsäuren, Carbonsäureester und Kohlensäureester lassen sich durch Umsetzung mit Antimonpentachlorid und Chlorwasserstoff in Acidiumsalze mit Wasserstoff am Oxonium-O-Atom überführen. Diese Acidiumsalze zeigen eine gewisse Chlorwasserstofftension und bilden mit einem zweiten Mol (bzw. bei den Carbonsäuren auch mehreren Molen) der zugehörigen Base H-Brücken-Addukte. Das Dimethyl-carbonatacidium-hexachloroantimonat konnte mittels Diazomethans zum Trimethyl-carbonatacidium-Salz methyliert werden.
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    URL: http://dx.doi.org/10.1002/cber.19590920814
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    Über ein Nitrosyl-kobalt-bis-acetylacetonat (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1858-1863 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Umsetzung von Kobalt(II)-acetylacetonat, gelöst in Methylenchlorid oder in fester Form, mit gasförmigem Stickoxyd wird ein tiefblaues, kristallines Nitrosyl-kobalt-bis-acetylacetonat rein dargestellt. Dieses ist in Äthylenbromid und anderen organischen Lösungsmitteln monomer löslich. Auf Grund von Leitfähigkeitsmessungen erweist es sich als Nichtelektrolyt und somit als ein Komplex der Koordinationszahl 5. Die aus dem magnetischen Verhalten und dem IR-Spektrum sich ergebenden Bindungsverhältnisse werden diskutiert.
    Additional Material: 2 Ill.
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    URL: http://dx.doi.org/10.1002/cber.19590920818
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    Über Actinomycetenfarbstoffe, VI. Pyrromycinone (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1880-1903 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus einem Streptomyces-Stamm wurden drei kristallisierte, als ν-, ζ-und ∊-Pyrromycinon bezeichnete Farbstoffe isoliert. ν-Pyrromycinon ist ein 1.4.6-Trihydroxy-carbomethoxy-äthyl-tetracenchinon, ζ- und ∊-Pyrromycinon sind Derivate des 1.4.6-Trihydroxy-7.8.9.10-tetrahydro-tetracenchinons mit einer Carbomethoxygruppe, einer Äthylgruppe und einer bzw. zwei Hydroxygruppen. Durch Dehydrierung bzw. Wasserabspaltung lassen sie sich in ν-Pyrromycinon überführen. Für alle drei Pyrromycinone werden Konstitutionsformeln aufgestellt. Die Pyrromycinone stehen den Rhodomycinonen nahe, mit denen sie über das aus ν-Pyrromycinon dargestellte ν-Iso-pyrromycinon strukturell verknüpft werden konnten.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920821
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    Säureamid-Reaktionen, XVII. Über die Umsetzung von Formamid mit Methyläthylketon in der Gasphase (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1918-1920 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Umsetzung von Formamid mit Methyläthylketon über Aluminiumoxyd führt bei 350-360° zu α-Amino-methyläthylacetonitril, bei 250-260° zu N-[α-Amino-isovaleryl]-N′-[2-imino-5-methyl-3.5-diäthyl-pyrrolidinyl-(3)]-harnstoff.
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    Untersuchungen in der Azolreihe, XII. 2-Amino-oxazole (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1944-1949 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: α-Halogen-ketone setzen sich mit Harnstoff, N-mono- und N.N-disubstituierten Harnstoffen in Dimethylformamid als Lösungsmittel zu 2-Amino-oxazolen um. Auf ihre Umwandlung in 2-Amino-imidazole wird hingewiesen.
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    Heterosubstituierte Acetylene, II. Darstellung und Reaktionen von Lithium-chloracetylenid in Äther (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1950-1956 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus den drei isomeren Dichloräthylenen kann mit Methyl-lithium in Äther Lithium-chloracetylenid (I) dargestellt werden, während Äthylmagnesiumbromid praktisch unwirksam ist. Die metallorganischen Eigenschaften von I werden zur Synthese organischer Chloracetylen-Derivate ausgenützt.
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    Berichtigung (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1982-1982 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920835
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    Über das Verhalten von Dehydrobenzol gegenüber nucleophilen und elektrophilen ReagenzienHerrn Professor Dr. Dr. h. c. St. Goldschmidt zum 70. Geburtstag (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1999-2013 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die bereits früher durchgeführten Umsetzungen von ortho-metalliertem Halogenbenzol mit tertiären Aminen, wie Triäthylamin, zu phenylierten tertiären Aminen lassen sich mit einem nucleophilen Angriff der Base auf Dehydrobenzol interpretieren. Zwingendere Argumente für ein intermediäres Auftreten von Dehydroaromaten liefert das Verhalten von orthometalliertem α- und β-Halogennaphthalin gegenüber Triäthylamin, da hierbei ein und dasselbe isomerenfreie β-Diäthylamino-naphthalin entsteht. Dafür spricht auch die Dien-Reaktion von Dehydronaphthalin mit Furan zum Endoxyd XII.  -  Orthometalliertes Halogenbenzol vermag auch mit elektrophilen Partnern wie Triäthylbor zu reagieren. Gleichzeitige Einwirkung von Triphenylbor und Triphenylphosphin führt zum Betain XV.
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    Die Reduktion von Carbonylverbindungen mit dem Komplex aus Calciumhydrid und TrimethylboratHerrn Prof. Dr. Dr. h. c. St. Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2022-2025 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Beim Erhitzen von Calciumhydrid mit Borsäure-trimethylester entsteht ein komplexes Hydrid, das Carbonylverbindungen sehr spezifisch zu den Alkoholen reduziert.
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    C,C-Hydrogenolyse von tetra-kernalkylierten PhloracylophenonenHerrn Professor Dr.phi1. Dr. rer. nat. h.c. Stefan Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2029-2032 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus l-Acetyl-3.3.5-trimethyl-5-benzyl-cyclohexen-(1)-ol-(2)-dion-(4.6) wird bei Hydrierung in Gegenwart von Palladium der Benzylrest als Toluol hydrogenolytisch glatt abgespalten. Analoga mit Allyl- bzw. γ.γ-Dimethyl-allyl-Gruppen anstelle des Benzylrestes werden normal hydriert zum n-Propyl- bzw. Isoamyl-Derivat.
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    URL: http://dx.doi.org/10.1002/cber.19590920908
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    Reaktionen mit Pyryliumsalzen, III. Aromatische Verbindungen aus 2.4.6-Triphenylpyrylium-fluoroborat und Benzyl-lithium, Acetessigester, Acetylaceton und CyanessigesterHerrn Professor Dr. Dr. h. c. Stefan Goldschmidt in Verehrung zu seinem 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2042-2045 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 2.4.6-Trisubstituierte Pyryliumsalze lassen sich mit geeigneten Carbanionen in aromatische Verbindungen überführen. In Analogie zu der früher beschriebenen Reaktion mit Metallsalzen des Nitromethans, wobei Derivate des Nitrobenzols entstehen, werden mit Benzyl-lithium Derivate des Biphenyls, mit Acetessigester substituierte Benzoesäureester, mit Acetylaceton substituierte Acetophenone und mit Cyanessigester substituierte aromatische Nitrile erhalten.
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    URL: http://dx.doi.org/10.1002/cber.19590920912
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    Ester und Polyester von Phosphorsäure und Cycloalkylphosphonsäuren mit PhenolenHerrn Professor Dr. Dr. h. c. Stefan Goldschmidt zu seinem 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2051-2056 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Darstellung einiger Phosphorsäure-monoarylester-dichloride und Phosphorsäure-diarylester-monochloride und eines Phosphonsäure-dichlorids wird beschrieben, ebenso die Kondensation einiger dieser Chloride mit einigen Phenolen zu polymeren Phosphorsäure-phenolestern.
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    Reaktionen der Eisencarbonyle mit verschiedenartigen Basen, III. Umsetzungen mit Derivaten der Pyridinreihe und anderen N-BasenIn Erinnerung an die gemeinsamen Jahre in Würzburg und München und die nun 40 Jahre bestehende Freundschaft, Stefan Goldschmidt zu seinem 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2075-2085 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Umsetzungen des Eisenpentacarbonyls mit Derivaten der Pyridinreihe, z. B. Pyridin-aldehyd-(2) und koordinativ 2-zähligen Pyridin-aldehyd-(2)-imiden, wie dem Methyl- und Äthylimid, führen zu Octacarbonyldiferraten mit hexakoordiniertem Kation, z. B. [Fe(RN=CH—NC5H4)3][Fe2(CO)8]. Mitunter verläuft die Reaktion über eine tieffarbige Additionsverbindung des betr. Amins mit Pentacarbonyl, die beim Anil als 2 Fe(CO)5·C6H5N=CH—NC5H4 gefaßt wurde. Weiterhin entstehen im letzteren Fall mit Eisentetracarbonyl, wie auch mit Pyridin-aldehyd-(2)-p-tolil, ferner mit o-Phenylendiamin oder Bipyridyl-(2.2′) und Pentacarbonyl Hendecacarbonylrifterrate, während sich mit Isochinolin, Pyrrolidon und Methylpyrrolidon und Pentacarbonyl Tridecacarbonyltetraferrate bilden, z. B. die Verbindungen [Fe(RN=CH—NC5H4)3][Fe3(CO)11] oder [Fe(C4H6ON(CH3))4][Fe4(CO)13].  -  Die für die Carbonylferrate angenommene Struktur mit 2-, 3- und 4-kernigen Anionen wird schließlich durch IR-Absorptionsspektren gestützt. Insgesamt zeigen so die Ergebnisse den spezifischen Einfluß der betr. komplexbildenden Komponente auf den Reaktionstyp.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920918
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    Phosphororganische Verbindungen, XIX. Reduktion von Phosphorverbindungen mit AlkalimetallenHerrn Prof. Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2088-2094 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Phosphorhalogen-Verbindungen, quartäre Phosphoniumsalze, Phosphorsauerstoff- und Phosphorschwefel-Verbindungen können mit feinverteiltem Natrium zu Natriumphosphiden bzw. Phosphinen reduziert werden. Aus Natrium-phosphiden und Alkylhalogeniden sind quartäre Phosphoniumsalze leicht zugänglich.
    Additional Material: 1 Tab.
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    URL: http://dx.doi.org/10.1002/cber.19590920920
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    Alkinyloverbindungen von Übergangsmetallen, XIV. Alkinylokomplexe von Nickel(I)Herrn Professor Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2135-2140 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Mittels der Reaktion K4[Ni2(CN)6(CO)2] + 8KC ≡CR → K6[Ni2(C≡CR)8] + 2CO + 6KCN ( R = H, CH3, C6H5) werden die gelben explosiven Octa-alkinylo-diniccolate(I) in flüssigem Ammoniak rein dargestellt. Die zweikernige Struktur dieser Verbindungen wird durch ihren Diamagnetismus, ihre Salznatur durch Leitfähigkeitsmessung bewiesen.  -  IR-Messungen an dem als Ausgangsmaterial verwendeten K4[Ni2(CN)6(CO)2] lassen das Vorliegen ketoartiger CO-Brücken im Anion erkennen.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920928
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  • 95
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    Über bi- und polycyclische Azulene, XL. Azulenglyoxylsäuren und Azulencarbonsäuren, ihre Darstellung und Reduktion mit LithiumalanatHerrn Professor Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag zuggeeignet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2152-2163 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Azulen-1(bzw. 3)-glyoxylsäuren und -carbonsäuren wurden aus Azulenen und Oxalylbromid ohne Katalysatoren dargestellt. Die Reduktion von Azulenmonocarbonsäuren, -glyoxylsäuren und -dicarbonsäuren wurde untersucht. Die optischen Eigenschaften der erhaltenen Azulenderivate werden diskutiert.
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    URL: http://dx.doi.org/10.1002/cber.19590920930
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  • 96
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    Eine verbesserte Darstellung für Dichlor-tetramethyl-cyclobutenHerrn Professor Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2181-2184 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Das in der Überschrift genannte Cyclobutenderivat kann aus Butin-(2) und Chlor bei Anwesenheit von Borfluorid in 45-proz. Ausbeute gewonnen werden.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920933
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  • 97
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    Die Umwandlung der Hypophosphorsäure in Diphosphor(III, V)-säureHerrn Prof. Dr. Dr. h. c. St. Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2199-2205 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei der Umwandlung von wasserfreier Hypophosphorsäure erfolgt eine Isomerisierung zu Diphosphor(III,V)-säure. Daneben tritt Oxydoreduktion zu Pyrophosphorsäure und pyrophosphoriger Säure ein. Einige neu vermessene Raman-Spektren von Oxosäuren des Phosphors und deren Salzen werden mitgeteilt.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920936
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    Zur Kenntnis des Verhaltens von Nichtmetallchalkogeniden gegenüber flüssigem Ammoniak, IV. Das Verhalten von Tetraphosphor-pentasulfid gegenüber flüssigem AmmoniakHerrn Prof. Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2252-2257 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die bei der Umsetzung von Tetraphosphor-pentasulfid, P4S5, mit flüssigem Ammoniak entstehenden Ammoniumverbindungen mit vier Phosphor- und fünf Schwefelatomen in der Molekel disproportionieren sich oberhalb von 140° in Tetraphosphor-trisulfid, P4S3, und Tetraphosphor-heptaimido-trisulfid, P4S3(NH)7. Außerdem bilden sich in Nebenreaktionen (ca. 10%) P4S7(NH)3, P4S10 und P4S7. Die Reaktionsmechanismen der Disproportionierungen, die Trennung der hierbei entstehenden Verbindungen und deren Eigenschaften werden beschrieben.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.19590920942
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  • 99
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    Cyclische Disulfide, III. cis- und trans-2.3-Dithia-decalinHerrn Professor Dr. Dr. h. c. Stefan Goldschmidt zum 70. Geburtstag zugeeignet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2271-2277 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: cis- und trans-2.3-Dithia-decalin werden auf zwei Wegen dargestellt, ihre Eigenschaften mit denen ähnlicher cyclischer Disulfide verglichen, die Konstellationen diskutiert.
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    URL: http://dx.doi.org/10.1002/cber.19590920945
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    Pyrrol-Chinon-FarbstoffeHerrn Professor Dr. Dr. h. c. St. Goldschmidt zum 70. Geburtstag gewidmet (1959)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 2026-2029 
    Details
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Pyrrol-Chinon-Farbstoffe sind auf Grund der jetzigen Erfahrungen über die Mechanismen der Pyrrolreaktionen und die Bildung von Pyrrolfarbstoffen als Dipyrrylchinone zu formulieren.
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    URL: http://dx.doi.org/10.1002/cber.19590920907
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