ALBERT — All Library Books, journals and Electronic Records Telegrafenberg

1

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Relation Between Inflammables and Ignition Sources in Aircraft Environments (1950)

Scull, Wilfred E

In: CASI

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Publikationsdatum: 2019-06-28

Beschreibung: A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and, discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presented and discussed. The ignition temperatures and the limits of inflammability of gasoline in air in different test environments, and the minimum ignition pressure and the minimum size of openings for flame propagation of gasoline - air mixtures are included. Inerting of gasoline - air mixtures is discussed.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-TN-2227

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2

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An Analysis of the Autorotative Performance of a Helicopter Powered by Rotor-Tip Jet Units (1950)

Gessow, Alfred

In: CASI

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Publikationsdatum: 2019-06-28

Beschreibung: The autorotative performance of an assumed helicopter was studied to determine the effect of inoperative jet units located at the rotor-blade tip on the helicopter rate of descent. For a representative ramjet design, the effect of the jet drag is to increase the minimum rate of descent of the helicopter from about 1,OO feet per minute to 3,700 feet per minute when the rotor is operating at a tip speed of approximately 600 feet per second. The effect is less if the rotor operates at lower tip speeds, but the rotor kinetic energy and the stall margin available for the landing maneuver are then reduced. Power-off rates of descent of pulse-jet helicopters would be expected to be less than those of ramjet. helicopters because pulse jets of current design appear to have greater ratios of net power-on thrust to power-off, drag than currently designed rain jets. Iii order to obtain greater accuracy in studies of autorotative performance, calculations in'volving high power-off rates of descent should include the weight-supporting effect of the fuselage parasite-drag force and the fact that the rotor thrust does not equal the weight of the helicopter.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-TN-2154

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3

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Investigation of the NACA 4-(3)(8)-045 Two-blade Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance (1950)

Delano, James B ; Stack, John ; Draley, Eugene C ; [weitere]

In: CASI

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Publikationsdatum: 2019-06-28

Beschreibung: As part of a general investigation of propellers at high forward speeds, tests of two 2-blade propellers having the NACA 4-(3)(8)-03 and NACA 4-(3)(8)-45 blade designs have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.725 to establish in detail the changes in propeller characteristics due to compressibility effects. These propellers differed primarily only in blade solidity, one propeller having 50 percent and more solidity than the other. Serious losses in propeller efficiency were found as the propeller tip Mach number exceeded 0.91, irrespective of forward speed or blade angle. The magnitude of the efficiency losses varied from 9 percent to 22 percent per 0.1 increase in tip Mach number above the critical value. The range of advance ratio for peak efficiency decreased markedly with increase of forward speed. The general form of the changes in thrust and power coefficients was found to be similar to the changes in airfoil lift coefficient with changes in Mach number. Efficiency losses due to compressibility effects decreased with increase of blade width. The results indicated that the high level of propeller efficiency obtained at low speeds could be maintained to forward sea-level speeds exceeding 500 miles per hour.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-TR-999

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4

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The Supersonic Axial-Flow Compressor (1950)

Kantrowitz, Arthur

In: CASI

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Publikationsdatum: 2019-06-28

Beschreibung: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-TR-974 , NACA-ACR-L6D02 , NACA-AR-36

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5

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Theoretical Investigations on the Efficiency and the Conditions for the Realization of Jet Engines (1950)

Roy, Maurice

In: CASI

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Publikationsdatum: 2019-08-16

Beschreibung: Contents: Preliminary notes on the efficiency of propulsion systems; Part I: Propulsion systems with direct axial reaction rockets and rockets with thrust augmentation; Part II: Helicoidal reaction propulsion systems; Appendix I: Steady flow of viscous gases; Appendix II: On the theory of viscous fluids in nozzles; and Appendix III: On the thrusts augmenters, and particularly of gas augmenters

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-TM-1259

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6

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Performance of J33-A-27 Turbojet-Engine Compressor (1950)

Beede, William L. ; Withee, Joseph R., Jr. ; Ginsburg, Ambrose

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50F14

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7

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Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine. II - Performance of Revised Compressor at Design Equivalent Speed (1950)

Creagh, John W. R.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: The compressor from the XT-46 turbine-propeller engine was revised by removing the last two rows of stator blades and by eliminating the interstage leakage paths described in a previous report. With the revised compressor, the flow choking point shifted upstream into the last rotor-blade row but the maximum weight flow was not increased over that of the original compressor. The flow range of the revised compressor was reduced to about two-thirds that obtained with the original compressor. The later stages of the compressor did not produce the design static-pressure increase probably because of excessive boundary-layer build-up in this region. Measurements obtained in the ninth-stage stator showed that the performance up to this station was promising but that the last three stages of the compressor were limiting the useful operating range of the preceding stages. Some modifications in flow-passage geometry and blade settings are believed to be necessary, however, before any major improvements in over-all compressor performance can be obtained.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50J10

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8

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Summary of Investigations of Mark 25 Aerial-Torpedo Turbine (1950)

Schum, Harold J. ; Whitney, Warren J. ; Buckner, Howard A., Jr.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: The power plant from a Mark 25 aerial torpedo was investigated both as a two-stage turbine and as a single-stage modified turbine to determine the effect on overall performance of nozzle size and shape, first-stage rotor-blade configuration, and axial nozzle-rotor running clearance. Performance was evaluated in terms of brake, rotor, and blade efficiencies. All the performance data were obtained for inlet total to outlet static pressure ratios of 8, 15 (design), and 20 with inlet conditions maintained constant at 95 pounds per square inch gage and 1000 F for rotor speeds from approximately 6000 to 18,000 rpm.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50D12

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9

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The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332 (1950)

Hall, James R. ; Sandahl, Carl A.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0. A corresponding change in nose shape for the winged models decreased the drag coefficient by about 0.05 in the Mach number range from 1.1 to 1.4; at Mach numbers greater than 1.6 no measurable reduction in drag coefficient was obtained. The drag of the present Sparrow fuselage is less than that of a parabolic fuselage which could contain the same equipment.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50C16a

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10

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Hydrodynamic Properties of Planing Surfaces and Flying Boats (1950)

Sokolov, N. A.

In: CASI

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Publikationsdatum: 2019-08-13

Beschreibung: The study of the hydrodynamic properties of planing bottom of flying boats and seaplane floats is at the present time based exclusively on the curves of towing tests conducted in tanks. In order to provide a rational basis for the test procedure in tanks and practical design data, a theoretical study must be made of the flow at the step and relations derived that show not only qualitatively but quantitatively the inter-relations of the various factors involved. The general solution of the problem of the development of hydrodynamic forces during the motion of the seaplane float or flying boat is very difficult for it is necessary to give a three-dimensional solution, which does not always permit reducing the analysis to the form of workable computation formulas. On the other had, the problem is complicated by the fact that the object of the analysis is concerned with two fluid mediums, namely, air and water, which have a surface of density discontinuity between them. The theoretical and experimental investigations on the hydrodynamics of a ship cannot be completely carried over to the design of floats and flying-boat hulls, because of the difference in the shape of the contour lines of the bodies, and, because of the entirely different flow conditions from the hydrodynamic viewpoint.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-TM-1246 , Materialy po Gidrodinamicheskomu Raschetu Glisserov i Gidrosamoletov; 1-39; CAHI-Rept-149

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11

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Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile (1950)

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL9D28

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12

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Ditching Investigation of a 1/15-Scale Model of the Convair-Liner Airplane (1950)

Thompson, William C. ; Fisher, Lloyd J.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: A ditching investigation of a model of the Convair-Liner airplane was made to observe the behavior and determine the safest procedure for making an emergency water landing. The ditching model was designed and constructed by the National Advisory Committee for Aeronautics. Design information on the airplane was furnished by the Consolidated Vultee Aircraft Corporation. A three-view drawing of the airplane is shown. The investigation was made in calm water at the Langley tank no. 2 monorail.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50K02

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13

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Gust-Tunnel Investigation to Determine the Load at the Joint of a Coupled Airplane Configuration Encountering a Gust (1950)

Cahen, George L.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation has been made in the Langley gust tunnel with two identical airplane models approximating 1/40-scale models of the B-29, coupled in tandem with a boom so that the individual centers of gravity were equidistant from the single coupling joint at the tail of the lead airplane. Time histories of the boom joint load were obtained as the models were flown through a gust. The results indicate that on a similar configuration involving airplanes the size of B-29 airplanes a load on the boom joint of 10,000 to 14,000 pounds could be induced by encountering a gust of 50 feet per second and having a gradient distance of 17 chords, at a forward speed of 380 feet per second and that the total load is extremely sensitive to the steadiness of flight that can be maintained with or without a gust. It is felt that the results are probably satisfactory to show order of magnitude, but it does not appear possible that a precise determination of the joint load that would be applicable to the full-scale airplanes can be obtained by gust-tunnel tests.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL51E01A

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14

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Summary of the Aerodynamic Characteristics and Flying Qualities Obtained from Flights of Rocket-Propelled Models of an Airplane Configuration Incorporating a Sweptback Inversely Tapered Wing at Transonic and Low-Supersonic Speeds (1950)

Mitcham, Grady L. ; Blanchard, Willard S., Jr.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: Flight tests have been conducted on rocket-propelled models of an airplane configuration incorporating a sweptback wing with inverse taper to investigate the drag, stability, and control characteristics at transonic and supersonic speeds. The models were tested with a conventional tail arrangement in the Mach number range from 0.55 to 1.2. In addition to the various aerodynamic parameters obtained, the flying qualities were computed for a full-scale airplane with the center-of-gravity location at 18 percent of the mean aerodynamic chord. Also, included in this investigation are drag measurements made on relatively simple fixed-control models tested with both conventional and V-tail arrangements.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-L50G18a

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15

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Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag (1950)

Stevens, Joseph E.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was encountered. The ratio of tip helix angle to aileron deflection indicated a decrease in proportional rolling effectiveness with increasing deflections in the Mach number range from approximately 0.7 to 1.0. A drag rise of about 125 percent in the transonic region between Mach numbers of 0.85 and 1.02 followed by a gradual decrease at higher speeds was revealed.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL51D27

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16

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Ditching Investigation of a 1/24-Scale Model of the Boeing B-47 Airplane (1950)

Windham, John O. ; Fisher, Lloyd J.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation of a 1/24-scale dynamically similar model of the Boeing B-47 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves. The airplane should be ditched at the lowest speed and highest attitude consistent with adequate control; the flaps should be full down. The airplane will probably make a deep but fairly smooth run. The fuselage bottom will be damaged and partially filled with water; consequently, crew members should be assigned ditching stations near an exit in the upper or forward part of the fuselage. The nacelles may be expected to be torn away from the wing. In calm water the maximum decelerations will be about 3g and the landing run will be about 6 fuselage lengths.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50E03

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17

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Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Similar to One Proposed by Douglas Aircraft Company, Inc. (1950)

Hewes, Donald E.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: At the request of the Air Materiel Command, an investigation was made in the Langley free-flight tunnel to determine the longitudinal stability and control characteristics of models coupled together in a tandem configuration for aerial refueling similar to one proposed by the Douglas Aircraft Company, Inc. Static force tests were made with 1/20-scale models of the B-29 and F-80 airplanes to determine the effects of rigidly coupling the airplanes together. The Douglas configuration differs from the rigid configuration tested in that it provides for some freedom in pitch and vertical displacement. The force tests showed that, for the bomber alone, the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration with rigid coupling the aerodynamic center was 0.28 mean aerodynamic chord forward of the center of gravity of the combination (unstable). This reduction in stability was caused by the downwash of the bomber on the fighter. The pitching moment produced by elevator deflection of the bomber was reduced approximately 50 percent by addition of the fighter. Some recent flight tests made in the free-flight tunnel on models in a similar tandem configuration indicated that, with a hinged coupling permitting freedom in pitch, the stability of the combination was better than that obtained with a rigid coupling and was about the same as that for the bomber alone.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50E01

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18

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Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Proposed by All American Airways, Inc. (1950)

Hewes, Donald E.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: At the request of the Air Materiel Command an investigation was made in the Langley free-flight tunnel to determine the static longitudinal stability and control characteristics of models coupled together in a tandem configuration proposed by All American Airways, Inc. Force tests were made using 1/20-scale models of B-29 end F-80 airplanes to determine the effects of coupling the fighter to the tail of the bomber. The results of the investigation showed that for the bomber alone the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration the aerodynamic center was 0.09 mean aerodynamic chord forward of the center of gravity, of the combination (unstable). The elevator effectiveness of the bomber was reduced approximately 50 percent by addition of the fighter. Some recent flight tests made in the free-flight tunnel with models simulating the proposed configuration indicate that the reduction in stability may be minimized by incorporating a hinged coupling permitting freedom in pitch.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50C14A

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19

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Effect of Various Modifications on Drag and Longitudinal Stability and Control Characteristics at Transonic Speeds of a Model of the XF7U-1 Tailless Airplane: NACA Wing-FLow Method, TED No. NACA DE 307 (1950)

Sawyer, Richard H. ; Trant, James P., Jr.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation was made by the NACA wing-flow method to determine the drag, pitching-moment, lift, and angle-of-attack characteristics at transonic speeds of various configurations of a semispan model of an early configuration of the XF7U-1 tailless airplane. The results of the tests indicated that for the basic configuration with undeflected ailavator, the zero-lift drag rise occurred at a Mach number of about 0.85 and that about a five-fold increase in drag occurred through the transonic speed range. The results of the tests also indicated that the drag increment produced by -8.0 degrees deflection of the ailavator increased with increase in normal-force coefficient and was smaller at speeds above than at speeds below the drag rise. The drag increment produced by 35 degree deflection of the speed brakes varied from 0.040 to 0.074 depending on the normal-force coefficient and Mach number. These values correspond to drag coefficients of about 0.40 and 0.75 based on speed-brake frontal area. Removal of the fin produced a small positive drag increment at a given normal-force coefficient at speeds during the drag rise. A large forward shift of the neutral-point location occurred at Mach numbers above about 0.90 upon removal of the fin, and also a considerable forward shift throughout the Mach number range occurred upon deflection of the speed brakes. Ailavator ineffectiveness or reversal at low deflections, similar to that determined in previous tests of the basic configuration of the model in the Mach number range from about 0.93 to 1.0, was found for the fin-off configuration and for the model equipped with skewed (more highly sweptback) hinge-line ailavators. With the speed brakes deflected, little or no loss in the incremental pitching moment produced by deflection of the ailavator from O degrees to -8.00 degrees occurred in the Mach number range from 0.85 to 1.0 in contrast to a considerable loss found in previous tests with the speed brakes off.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50D18

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20

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Investigation of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Modified Chance Vought XF7U-1 Airplane. TED No. NACA DE 311 (1950)

Pumphrey, Norman E. ; Berman, Theodore

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks. The results indicated that the revision in the vertical tails did not greatly alter the spin and recovery characteristics of the model and recovery by normal use of controls (fill rapid rudder reversal followed approximately one-half turn later by movement of the stick forward of neutral) was satisfactory. Adding the external wing tanks to cause the recovery characteristics to become critical and border on an unsatisfactory condition; however, it was shown that satisfactory recovery could be obtained by jettisoning the tanks, followed by normal recovery technique.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50F02

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21

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Preliminary Results Obtained from Flight Test of a Rocket Model Having the Tail Only of the Grumman XF10F Airplane Configuration, TED No. NACA DE 354 (1950)

Edmondson, James L. ; Gardner, William N.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: A flight test was made to determine the servoplane effectiveness and stability characteristics of the free-floating horizontal stabilizer to be used on the XF10F airplane. The results of this test indicate that servoplane effectiveness is practically constant through the speed range up to a Mach number of 1.15, and the stabilizer static stability is satisfactory. A loss of damping occurs over a narrow Mach number range near M = 1.0, resulting in dynamic instability of the stabilizer in this narrow range. Above M = 1.0 there is a gradual positive trim change of the stabilizer.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL51E04

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22

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Preliminary Performance Data on General Electric Integrated Electronic Control Operating on J47 RX1-3 Turbojet Engine in NACA Altitude Wind Tunnel (1950)

Taylor, Burt L., III ; Blivas, Darnold

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: Performance data obtained with recording oscillographs are presented to show the transient response of the General Electric Integrated Electronic Control operating on the J47 RXl-3 turbo-Jet engine over a range of altitudes from 10,000 to 45,000 feet and at ram pressure ratios of 1.03 and 1.4. These data represent the performance of the final control configuration developed after an investigation of the engine transient behavior in the NACA altitude wind tunnel. Oscillograph traces of controlled accelerations (throttle bursts),oontrolled decelerations (throttle chops), and controlled altitude starts are presented.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50G12

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Free-Flight Investigation of the Static and Dynamic Longitudinal Stability Characteristics of 1/3.7-Scale Rocket-Powered Models of the Bell MX-776A (1950)

Michal, David H.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: An investigation of the static and dynamic longitudinal stability characteristics of 1/3.7 scale rocket-powered model of the Bell MX-776A has been made for a Mach number range from 0.8 to 1.6. Two models were tested with all control surfaces at 0 degree deflection and centers of gravity located 1/4 and 1/2 body diameters, respectively, ahead of the equivalent design location. Both models were stable about the trim conditions but did not trim at 0 degree angle of attack because of slight constructional asymmetries. The results indicated that the variation of lift and pitching moment was not linear with angle of attack. Both lift-curve slope and pitching-moment-curve slope were of the smallest magnitude near 0 degree angle of attack. In general, an increase in angle of attack was accompanied by a rearward movement of the aerodynamic center as the rear wing moved out of the downwash from the forward surfaces. This characteristic was more pronounced in the transonic region. The dynamic stability in the form of total damping factor varied with normal-force coefficient but was greatest for both models at a Mach number of approximately 1.25. The damping factor was greater at the lower trim normal-force coefficients except at a Mach number of 1.0. At that speed the damping factor was of about the same magnitude for both models. The drag coefficient increased with trim normal-force coefficient and was largest in the transonic region.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SL50B23

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Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air (1950)

Rousso, Morris D. ; Kochendorfer, Fred D.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: Investigations have been conducted to determine by means of total-pressure surveys the boundaries of single and twin jets discharging through convergent nozzles into quiescent air. The jet boundaries for the region from the nozzle outlets to a station 6 nozzle diameters downstream are presented for nozzle pressure ratios ranging from 2.5 t o 16.0 and for twin-Jet nozzle center-line spacings ranging from 1.42 to 2.50 nozzle diameters. The effects of these parameters on the interaction of twin Jets are discussed. In order to ascertain the utility of the results for other than the test conditions, the effects of jet temperature, Reynolds number, and humidity on the pressure boundaries have been briefly investigated. The result indicate that for a jet of 2.6 the pressure boundaries are slightly smaller than those of corresponding unheated jets and that the effects of Reynolds number and humidity are negligible.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-E50E03a

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Range Performance of Bombers Powered by Turbine-Propeller Power Plants (1950)

Cline, Charles W.

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: Calculations have been made to find range? attainable by bombers of gross weights from l40,000 to 300,000 pounds powered by turbine-propeller power plants. Only conventional configurations were considered and emphasis was placed upon using data for structural and aerodynamic characteristics which are typical of modern military airplanes. An effort was made to limit the various parameters invoked in the airplane configuration to practical values. Therefore, extremely high wing loadings, large amounts of sweepback, and very high aspect ratios have not been considered. Power-plant performance was based upon the performance of a typical turbine-propeller engine equipped with propellers designed to maintain high efficiencies at high-subsonic speeds. Results indicated, in general, that the greatest range, for a given gross weight, is obtained by airplanes of high wing loading, unless the higher cruising speeds associated with the high-wing-loading airplanes require-the use of thinner wing sections. Further results showed the effect of cruising at-high speeds, of operation at very high altitudes, and of carrying large bomb loads.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-L50F12 , Rept-3185

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Performance of J33-A-27 Turbojet-Engine Compressor (1950)

Beede, William L. ; Ginsburg, Ambrose

In: CASI

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Publikationsdatum: 2019-07-11

Beschreibung: A modified J33-A-27 compressor was operated over a range of equivalent impeller speeds from 6100 to 13,250 rpm in order to obtain the over-all compressor performance. At the equivalent design speed of 11,800 rpm, the maximum efficiency of 0.764 and peak pressure ratio of 4.56 occurred at an equivalent weight flow of 104.07 pounds per second. At the highest equivalent speed (13,250 rpm) a maximum efficiency of 0.711, a maximum equivalent weight flow of 123.00 pounds per second, and a peak pressure ratio of 5.76 were obtained.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50D25

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Investigation of Altitude Ignition, Acceleration, and Steady-State Operation with a Single Combustor of a J47 Turbojet Engine (1950)

Butze, Helmut F. ; Cook, William P.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: An investigation was conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady state operating characteristics. Satisfactory ignition was obtained with two modifications of the original opposite-polarity spark plug up to and including an altitude of 40,003 feet at conditions simulating equilibrium windmilling of the engine at a flight speed of 400 miles per hour. At a simulated altitude of 30,000 feet, satisfactory ignition was obtained over a range of simulated engine speeds. No significant effect of fuel temperature on ignition limits was observed over a range of fuel temperatures from 80 deg to -52 deg F. At an altitude of 30,000 feet, the excess temperature rise available for acceleration at low engine speeds was limited by the ability of the combustor to produce temperature rise, whereas at high engine speeds the maximum allowable turbine-inlet temperature became the restricting factor. Altitude operational limits increased from about 51,500 feet at 55 percent of rated engine speed to about 64,500 feet at 85 percent of rated speed. Combustion efficiencies varied from 59.0 to 92.6 percent over the range investigated and decreased with a decrease in engine speed and with an increase in altitude; higher efficiencies would have been obtained if lower altitudes had been investigated. Comparisons were made of the combustion efficiencies of weathered aviation gasoline and MIL-F-5616 fuel at altitudes of 30,000 and 40,000 feet. Combustion efficiencies obtained with MIL-F-5616 fuel were 8 percent higher at rated engine speed and 14 percent lower at 55 percent of rated speed than those obtained with weathered aviation gasoline.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-RM-SE50J12

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Notes on Factors Affecting Geometrical Arrangement of Tricycle-Type Landing Gear (1937)

Kantrowitz, A. R. ; Wenzinger, Carl J.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: The effects of the geometrical arrangement of tricycle landing gears on various characteristics of an airplane equipped with such landing gear is discussed. The characteristics discussed include directional stability, overturning tendencies, steering and ground handling, shimmy, takeoff, and porpoising. The conclusions are summarized in a table.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-SR-63

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The Transition Phase in the Take-Off of an Airplane, Special Report (1937)

Wetmore, J. W.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: An investigation was undertaken to determine the character and importance of the transition phase between the ground run and steady climb in the takeoff of an airplane and the effects of various factors on this phase and on the airborne part of the takeoff as a whole. The information was obtained from a series of step-by-step integrations, which defined the motion of the airplane during the transition and which were based on data derived from actual takeoff tests of a Verville AT airplane. Both normal and zoom takeoffs under several loading and takeoff speed conditions were considered. The effects of a moderate wind with a corresponding wind gradient and the effect of proximity of the ground were also investigated. The results show that, for normal takeoffs, the best transition was realized at the lowest possible takeoff speed. Moreover, this speed gave the shortest overall takeoff distance for normal takeoffs. Zoom takeoffs required a shorter overall takeoff run than normal takeoffs, particularly with a heavy landing, if the obstacle to be cleared was sufficiently high (greater than 50 feet); no advantage was indicated to the airplane with a light loading if the height to be cleared was less. The error resulting from the neglect of the transition in the calculation of the airborne distance of takeoff was found to vary from 4% with the heaviest loading considered to -4% with the lightest loading for normal takeoffs over a 100-ft obstacle; the percentage error was twice as great for a 50-foot obstacle. For zoom takeoffs the error attained much greater values. The average wind gradient corresponding to a 5-mile-per-hour surface wind reduced the airborne distance required to clear a 50-foot obstacle by about 9% with the lightest loading and 16% with the heaviest loading; for both cases. The overall reduction due to this wind was approximately twice that resulting from the wind gradient alone. A simple expression for the reduction of observed takeoff performance to no-wind conditions is presented. Ground effect is shown to reduce the airborne distance to attain a height of 50 foot by 10% with the lightest loading and 16% with the heaviest loading; for a 100-foot obstacle the percentage reduction was about 1/2 as great.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-SR-70

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Energy Loss, Velocity Distribution, and Temperature Distribution for a Baffled Cylinder Model, Special Report (1937)

Brevoort, Maurice J.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: In the design of a cowling a certain pressure drop across the cylinders of a radial air-cooled engine is made available. Baffles are designed to make use of this available pressure drop for cooling. The problem of cooling an air-cooled engine cylinder has been treated, for the most part, from considerations of a large heat-transfer coefficient. The knowledge of the precise cylinder characteristics that give a maximum heat-transfer coefficient should be the first consideration. The next problem is to distribute this ability to cool so that the cylinder cools uniformly. This report takes up the problem of the design of a baffle for a model cylinder. A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that the cooling can be improved 20% by using a correctly designed baffle. Such a gain is as effective in cooling the cylinder with the improved baffle as a 65% increase in pressure drop across the standard baffle and fin tips.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-SR-64

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Stability of Castering Wheels for Aircraft Landing Gears, Special Report (1937)

Kantrowitz, Arthur

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: In many installations of castering rubber-tired wheels there is a tendency for the wheel to oscillate violently about the spindle axis. This phenomenon, popularly called 'shimmy,' has occurred in some airplane tail wheels and has been corrected in two ways: first by the application of friction in the spindles of the tail wheels; and, second, by locking the wheels while taxiing at high speeds. Shimmy is common with the large wheels used as nose wheels in tricycle landing gears and, since it is impossible to lock the wheels, friction in the nose-wheel spindle has been the sole means of correction. Because the nose wheel is larger than the conventional tail wheel and usually carries a greater load, the larger amounts of spindle friction necessary to prevent shimmy are objectionable. the present paper presents a theoretical and experimental study of the problem of the stability of castering wheels for airplane landing gears. On the basis of simplified assumptions induced from experimental observations, a theoretical study has been made of the shimmy of castering wheels. The theory is based on the discovery of a phenomenon called 'kinematic shimmy' and is compared quantitatively with the results of model experiments. Experimental checks, using a model having low-pressure tires, are reported and the applicability of the results to full scale is discussed. Theoretical methods of estimating the spindle viscous damping and spindle solid friction necessary to avoid shimmy - lateral freedom - is introduced.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-SR-67

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Tandem Air Propellers (1937)

Lesley, E.P.

In: CASI

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Publikationsdatum: 2019-08-26

Beschreibung: Tests of 2-blade, adjustable-pitch, counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8 1/2%, 15% and 30% diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form. The tests showed that the efficiency of the tandem propellers was from 0.5% to 4% greater than that of a 4-blade propeller and, at the high pitch settings, not appreciable inferior to that of a 2-blade propeller. It was found that the rear tandem propeller should be set at a pitch angle slightly less than that of the forward propeller to realize the condition of equal power at maximum efficiency. Under this condition the total power absorbed by the tandem propellers was from 3% to 9% more than that absorbed by the 4-blade propeller and about twice that absorbed by a 2-blade propeller.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-SR-66

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Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine. I - Preliminary Investigation at 50-,70-, and 100-Percent Design Equivalent Speed (1950)

Sandercrock, Donald M. ; Creagh, John W.R.

In: CASI

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Publikationsdatum: 2019-07-12

Beschreibung: An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations. The station near the entrance section of the combustors indicated a peak pressure ratio of 6.3 at an adiabatic efficiency of 0.63 for a corrected weight flow of 23.1 pounds per second. The other, located one blade-chord downstream of the last stator row, indicated a peak pressure ratio of 6.97 at an adiabatic efficiency of 0.81 for a corrected weight flow of 30.4 pounds per second. The difference in performance obtained at the two stations is attributed to shock waves in the vicinity of the last stator row. These shock waves and the accompanying flow choking, together with interstage circulatory flows, shift the compressor operating curves into the region where surge would normally occur. The inability of the compressor to meet design pressure ratio is probably due to boundary-layer buildup in the last stages, which cause axial velocities greater than design values that, in turn, adversely affect the angles of attack and turning angles in these blade rows.

Schlagwort(e): Aircraft Propulsion and Power

Materialart: NACA-RM-SE50E22

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Vibration of a Wing of Finite Span in a Supersonic Flow (1950)

Haskind, M. D. ; Falkovich, S. V.

In: CASI

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Publikationsdatum: 2019-07-13

Beschreibung: An investigate ion was made of the disturbed motion of a gas for the harmonic vibrations of a thin slightly cambered wing of finite span moving forward with supersonic velocity. This problem was considered by E. A. Krasilshchikova who applied the method of Fourier series and obtained a solution of the space problem for the condition that the Mach cones drawn through the leading edge of the wing intersect the wing or are tangent to it. In this paper, a different method of solution is given, which is free from the previously mentioned condition. In particular, the vibrations of a triangular wing lying within the Mach cone are considered.

Schlagwort(e): Aircraft Design, Testing and Performance

Materialart: NACA-TM-1257 , Prikladnaya Matematika i Mekhanika; 11; 371-376

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Digitale Medien

Über den enzymatischen Abbau des Histamins I (1937)

Edlbacher, S. ; Zeller, A.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 717-726

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Es wird gezeigt, dass die enzymatische Histamin-Spaltung ein oxydativer Vorgang ist, bei dem ein Äquivalent Stickstoff in Form von Ammoniak in Freiheit gesetzt wird. Die Frage, ob dieses Stickstoff-Atom aus dem Kern stammt, ist auf Grund der analogen Modellversuche mit Ascorbinsäure und Eisenkatalyse wahrscheinlich im positiven Sinn zu beantworten, muss aber erst endgültig bewiesen werden. Auf Grund dieses Verhaltens muss das Enzym höchstwahrscheinlich als ein sogenanntes Häminferment angesehen werden. Bei der Histaminspaltung bildet sich ein Pigment. Ausserdem ist es gelungen, ein Keton in Form eines wohlcharakterisierten Dinitro-phenylhydrazons zu isolieren, dessen Konstitutionsermittlung im Gange ist.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001104

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Digitale Medien

Darstellung und Eigenschaften des Osazones der Dehydro-ascorbinsäure (1937)

Antener, I.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 742-746

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 4 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001107

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Digitale Medien

Constante diélectrique et moment dipolaire des maléate et fumarate d'éthyle et de leurs ozonides (1937)

Briner, E. ; Perrottet, E. ; Paillard, H. ; [weitere]

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 762-767

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Pour les constantes diélectriques et les moments dipolaires des maléate et fumarate l'éthyle et des ozonides de ces deux corps, les valeurs trouvées sont: .

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001109

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Digitale Medien

Propriétés des polymères en solution IV. Energie libre et chaleur de formation. Solutions de valérianate et de sébacate de butyle (1937)

Boissonnas, Ch. G.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 768-779

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: 1° Nous avons mesuré, par la méthode calorimétrique, les chaleurs de formation des mélanges binaires: .

Zusätzliches Material: 5 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001110

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Digitale Medien

Propriétés des polymères en solution V. Mesure des pressions de vapeur (1937)

Boissonnas, Ch. G. ; van der Wyk, A. J.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 779-782

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Description d'un appareillage pour la mesure précise et rapide de la pression de vapeur en équilibre avec une solution liquide on sous forme de gel. Cet appareil peut être utilisé avec des quantités de substances inférieures à 0,1 gr.

Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001111

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Polyterpene und Polyterpenoide CXII. Dehydrierungen in der Amyrinreihe (1937)

Ruzicka, L. ; Schellenberg, H. ; Goldberg, M. W.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 791-804

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001113

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Polyterpene und Polyterpenoide CXIII. Oxydationen in der Reihe der Oleanolsäure ohne Sprengung des Ringsystems. Über die Natur des vierten Sauerstoffatoms der Glycyrrhetinsäure (1937)

Ruzicka, L. ; Cohen, S. L.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 804-808

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001114

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Digitale Medien

Über Bestandteile der Nebennieren-Rinde IX (1937)

Steiger, Marguerite ; Reichstein, T.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 817-827

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001117

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Die Strukturformel des durch elektrochemische Reduktion von Methyl-benzyl-acetessigester gewonnenen Kohlenwasserstoffs C12H18 (Tafel'sche Umlagerung III) (1937)

Stenzl, Hans ; Fichter, Fr.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 846-851

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ISSN: 0018-019X

Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001119

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Digitale Medien

Commission des réactifs nouveaux. La classification des réactions qualitatives analytiques (1937)

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 852-852

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ISSN: 0018-019X

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URL: http://dx.doi.org/10.1002/hlca.193702001121

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Photolysen mit Zinksulfid (1937)

Gloor, Karl

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 853-877

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Notizen: 1. Es wird festgestellt, dass Farbstoffe vom Typus des Methylenblaus schwärzungsfähiges Zinksulfid desensibilieren.

Zusätzliches Material: 5 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001123

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Über die Desensibilierung von Anthrachinon-Farbstoffen und die Lichtbleiche von Geweben (1937)

Baur, Emil

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 879-881

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URL: http://dx.doi.org/10.1002/hlca.193702001125

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Eine Aufspaltung des Cumaronkerns (1937)

Reichstein, T. ; Baud, J.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 892-894

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URL: http://dx.doi.org/10.1002/hlca.193702001128

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Über 4,6-Diamino-1,3-diacetyl-benzol und seine Überführung in Derivate des lin. Benzo-dipyridins. (30. Mitteilung über Stickstoff-Heterocyclen) (1937)

Ruggli, Paul ; Reichwein, Heinrich

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 905-913

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URL: http://dx.doi.org/10.1002/hlca.193702001130

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Beitrag zur Indigosynthese aus o-substituierten Acetophenonen. (31. Mitteilung über Stickstoff-Heterocyclen) (1937)

Ruggli, Paul ; Reichwein, Heinrich

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 913-918

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URL: http://dx.doi.org/10.1002/hlca.193702001131

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Ein Apparat zur Extraktion von Lösungen mit schweren Lösungsmitteln (1937)

Wehrli, S.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 927-931

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URL: http://dx.doi.org/10.1002/hlca.193702001134

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Über einige thermische Eigenschaften des Vinylbromids (1937)

Guyer, A. ; Schütze, H. ; Weidenmann, M.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 936-949

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Notizen: 1. Es wurde die Dampfdruckkurve von Vinylbromid in dem Temperaturbereich von - 80° bis + 50° bestimmt.

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URL: http://dx.doi.org/10.1002/hlca.193702001136

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Über die thermische Zersetzung von Di-benzoyl-peroxyd in Gegenwart von Deuterium (1937)

Erlenmeyer, H. ; Schoenauer, W.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1015-1016

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URL: http://dx.doi.org/10.1002/hlca.193702001146

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Zur Kenntnis der 1-Amino-2-methyl-naphtalin-4-sulfosäure (1937)

Fierz-David, Hans Eduard ; Mannhart, Emil

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1024-1040

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Notizen: 1. Die Nitrierung des 2-Methyl-naphtalins wurde nach verschiedenen Methoden durchgeführt. Man erhält zur Hauptsache 1-Nitro-2-methyl-naphtalin.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001149

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d- und l-Tagato-methylose (1937)

Barnett, J. ; Reichstein, T.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1529-1536

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URL: http://dx.doi.org/10.1002/hlca.193702001203

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Polyterpene und Polyterpenoide CXX. Umwandlung der Oleanolsäure in β-Amyrin und Erythro-diol (1937)

Ruzicka, L. ; Schellenberg, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1553-1556

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URL: http://dx.doi.org/10.1002/hlca.193702001206

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Polyterpene und Polyterpenoide CXXII. Nachweis einer Doppelbindung in der Chinovasäure (1937)

Ruzicka, L. ; Prelog, V.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1570-1575

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Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001209

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Über Amminkomplexe von Schwermetallsalzen der Adipinsäure (1937)

Maritz, Alfred

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1575-1578

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URL: http://dx.doi.org/10.1002/hlca.193702001210

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Protokoll (1937)

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1603-1604

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URL: http://dx.doi.org/10.1002/hlca.193702001214

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Bei der Redaktion eingelaufene Bücher (1937)

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1604-1604

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URL: http://dx.doi.org/10.1002/hlca.193702001215

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Bemerkung zu der Chlorierung von Nitrobenzol in Gegenwart von Eisen(III)chlorid (1937)

Fierz-David, Hans Eduard ; Stähelin, Friedrich Rudolf

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1458-1461

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Notizen: Bei der Chlorierung von trockenem Nitrobenzol mit trockenem Chlor in Gegenwart von wasserfreiem Eisen(III)chlorid bilden sich bei 40° m-Nitrochlorbenzol, 1,2-Nitrochlorbenzol, 1,4-Nitrochlorbenzol und 2,5-Dichlor-nitrobenzol. Geht man bei der Chlorierung auf höhere Temperaturen, so bilden sich beträchtliche Mengen an Hexachlorbenzol, welches aus dem Nitrobenzol entsteht und nicht aus Benzol.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001196

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Sur la production de l'ozone par l'électrolyse. Electrolyse à basse température (1937)

Briner, E. ; Hæfeli, R. ; Paillard, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1510-1523

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Notizen: En vue d'augmenter le rendement de production de l'ozone par électrolyse, celle-ci a été opérée en réfrigérant énergiquement l'anolyte.

Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001201

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l-Tagatose (1937)

Glatthaar, C. ; Reichstein, T.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1537-1541

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URL: http://dx.doi.org/10.1002/hlca.193702001204

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Zur Kenntnis der flüchtigen Pflanzenstoffe V. Über die Darstellung des Grundkörpers der Azulen-Reihe (1937)

Plattner, Pl. A. ; St. Pfau, Alexander

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 224-232

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Thema: Chemie und Pharmazie

Notizen: 1. Darstellung und Eigenschaften des Azulens, Bicyclo-[0,3,5]-decapentaen-(1,3,5,7,9), wurden beschrieben.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200133

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Sexualhormone XX. Herstellung von Oxyden aus Δ5-Cholestenon und aus Δ5-Androstendion (1937)

Ruzicka, L. ; Bosshard, Werner

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 244-249

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URL: http://dx.doi.org/10.1002/hlca.19370200135

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Absorptionsspektrophotometrie von Lösungen im kurzwelligen Ultraviolett (1937)

Mohler, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 282-285

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Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200139

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Lichtabsorption der R1-R1-Systeme I. Spektren von Cholestenon, Cholestenon-oxim, Mesityloxyd, Pulegon und Carvon (1937)

Mohler, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 289-293

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Zusätzliches Material: 2 Ill.

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URL: http://dx.doi.org/10.1002/hlca.19370200142

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Sur une nouvelle synthèse de l'alcool anisique (1937)

Ofner, Alfred

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 53-55

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URL: http://dx.doi.org/10.1002/hlca.19370200105

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Zur Konstitution der Lactoflavin-phosphorsäure aus Leber (1937)

Karrer, P. ; Frei, P. ; Meerwein, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 79-83

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URL: http://dx.doi.org/10.1002/hlca.19370200108

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Reduktionsprodukte von Disacchariden: Maltit, Lactit, Cellobit (1937)

Karrer, P. ; Büchi, J.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 86-90

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URL: http://dx.doi.org/10.1002/hlca.19370200110

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Polyterpene und Polyterpenoide CXI. Über die Bruttoformel der Glycyrrhetinsäure (1937)

Ruzicka, L. ; Furter, M. ; Leuenberger, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 312-325

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Zusätzliches Material: 4 Tab.

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URL: http://dx.doi.org/10.1002/hlca.19370200146

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Atomgewichte 1937 (1937)

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 346-346

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URL: http://dx.doi.org/10.1002/hlca.19370200150

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Bei der Redaktion eingelaufene Bücher (1937)

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 352-352

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URL: http://dx.doi.org/10.1002/hlca.19370200154

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Recherches sur les réactifs organiques, susceptibles d'applications à l'analyse minérale. I. La 9-méthyle-2-3-7-trioxy-6-fluorone, réactif spécial des cations de l'antimoine (1937)

Duckert, Roger

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 362-367

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URL: http://dx.doi.org/10.1002/hlca.19370200157

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Nochmals zur Frage der Existenz von Querelementen in den nativen vegetabilische Gespinstfasern (1937)

Haller, R.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 199-203

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Zusätzliches Material: 5 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200125

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Bemerkung zur Notiz von Y. Asahina und S. Takagi über das Artemisia-keton (1937)

Ruzicka, L.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 221-221

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Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200131

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Positions des atomes dans le nouveau modèle spatial de la cellulose (1937)

Meyer, Kurt H. ; Misch, Lore

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 232-244

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Partant d'un modèle de la cellobiose, dans lequel les angles et les distances interatomiques sont en harmonie avec les données actuelles, un nouveau modèle spatial de la cellulose a été construit. Dans ce modèle, les deux chaînes cellobiosiques qui traversent la maille élémentaire parallèlement à l'axe, b, ont des directions opposées. Les paramètres des atomes ont été trouvés à l'aide des intensités relatives des interférences aux Rayons X.

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URL: http://dx.doi.org/10.1002/hlca.19370200134

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77

Digitale Medien

Molekulare Resonanzsysteme II. Herstellung und Eigenschaften substituierter Anilin-sulfon-phtaleine (1937)

Schwarzenbach, G. ; Ott, G. H. ; Hagger, O.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 498-513

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200176

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78

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Contribution à l'étude de la 2,3-naphtylène-diamine (1937)

Goldstein, Henri ; Streuli, Max

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 520-524

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200179

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79

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Zur Kenntnis des Kohlenstoffringes XXXI. Über die Beziehungen zwischen Schmelzpunkt und Dichte in aliphatischen und cyclischen homologen Reihen (1937)

Ruzicka, L. ; Giacomello, G.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 548-562

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 2 Ill.

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URL: http://dx.doi.org/10.1002/hlca.19370200182

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80

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Bericht zur Jahresrechnung per 31. Dezember 1936 (1937)

Engi, G.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 570-572

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200186

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81

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Reduktionswirkungen des N-Glucosido-o-dihydro-nicotinsäureamids und analoger Verbindungen (1937)

Karrer, P. ; Ringier, B. H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 622-625

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200191

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82

Digitale Medien

Glucosaminol, ein Reduktionsprodukt des Glucosamins (1937)

Karrer, P. ; Meyer, J.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 626-627

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200192

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83

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Die Verschiebungsregel des Geschwindigkeitsmaximums der bimolekularen heterogenen Reaktion (1937)

Reichinstein, D.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 644-647

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 1 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200195

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84

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Molekulare Resonanzsysteme IV. Die Absorptionsspektren einiger Sulfon-phtaleine (1937)

Mohler, H. ; Forster, H. ; Schwarzenbach, G.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 654-658

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 15 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.19370200198

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85

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Über die Synthese eines Glycerin-d1 aus optisch-aktivem Aceton-d-glycerinaldehyd (1937)

Erlenmeyer, H. ; Fischer, Hermann O. L. ; Baer, Erich

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1012-1014

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001145

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86

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β-Apo-4-carotinal, ein weiteres Abbauprodukt des β-Carotins (1937)

Karrer, P. ; Solmssen, U. ; Gugelmann, W.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1020-1024

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 2 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001148

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87

Digitale Medien

Δ5-3-Oxy-ätio-cholensäure und einige ihrer Umwandlungsprodukte (1937)

Steiger, Marguerite ; Reichstein, T.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1040-1054

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001150

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88

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Über die Einwirkung primärer aliphatischer Basen auf Campherchinon II (1937)

Rupe, H. ; di Vignano, Angelo Tommasi

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1078-1097

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 2 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001153

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89

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Zur Bestimmung von Vitamin B1 im menschlichen Harn (1937)

Karrer, Walter

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1147-1155

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 3 Tab.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001156

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90

Digitale Medien

Azofarbstoffe und Immunbiologie. Aufhebung anaphylaktischer Azoprotein-Überempfindlichkeit durch p-Phenyl-arsinsäure-azofarbstoffe (1937)

Fierz, H. E. ; Jadassohn, W. ; Stoll, W. G.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1059-1077

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: 1. Azoprotein (sowohl in vitro hergestelltes als in vivo entstehendes) enthält entsprechend der Annahme von Pauly die Azo-gruppierung —N=N—.

Zusätzliches Material: 3 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001152

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91

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Chemische Kampfstoffe V. Diskussion der Absorptionsbande von β,β′-Dichlor-diäthyl-sulfid (1937)

Mohler, H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1188-1192

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Zusätzliches Material: 2 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001161

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92

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Polyterpene und Polyterpenoide CXVI. Zur Kenntnis der Oxydation der Acetyl-oleanolsäure mit Chromtrioxyd unter Öffnung der Doppelbindung (1937)

Ruzicka, L. ; Cohen, S. L.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1192-1200

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001162

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93

Digitale Medien

Synthesen niederer Methyl-zucker (1937)

Fischer, Hermann O. L. ; Baer, Erich ; Pollock, Heinz ; [weitere]

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1213-1226

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001166

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94

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Polyterpene und Polyterpenoide CXVII. Zur Kenntnis der Bedingungen und des Mechanismus der Dehydrierung der homologen Sterine und der Cholsäure (1937)

Ruzicka, L. ; Goldberg, M. W.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1245-1253

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Schlagwort(e): Chemistry ; Organic Chemistry

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Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001169

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95

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Über Chinonreaktionen (1937)

Woker, G. ; Antener, I.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1260-1270

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001171

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96

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Sexualhormone XXVI. Zur Kenntnis der Oxydation von Cholesterin-acetat-dibromid mit Chromtrioxyd (1937)

Ruzicka, L. ; Fischer, Werner H.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1291-1297

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001175

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97

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Krystallisiertes l-Threonsäure-lacton und Synthese des l-Threonsäure-2-methyläthers (1937)

Gätzi, K. ; Reichstein, T.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1298-1303

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001176

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98

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Propriétés de polymères en solution VIII. Formation de micelles dans les solutions de substances à molécules caténiformes (1937)

Meyer, Kurt H. ; van der Wyk, A.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1321-1330

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: Les mêmes causes qui déterminent l'insolubilité des paraffines: la forte cohésion du dissolvant ainsi que l'attraction mutuelle des méthylènes provoquent une association des chaînes paraffiniques. Cette association se traduit par la présence, dans la solution, de micelles.

Zusätzliches Material: 5 Ill.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001181

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99

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Les propriétés des polymères en solution IX. Gélatinisation (1937)

Meyer, Kurt H. ; van der Wyk, A.

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1331-1334

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Notizen: La solubilité de substances polymérisées varie d'autant plus rapidement avec la température que le degré de polymérisation est plus élevé. Cela permet d'expliquer l'apparition de «points» de transformation dans les expériences avec des solutions de polymères supérieures. La formation thermo-réversible de gelées est le plus souvent une sorte de cristallisation.

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001182

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100

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Zur Kenntnis der Eigenschaften isosterer und strukturähnlicher Verbindungen III: Über die Synthese in 5-Stellung geminal substituierter 2,4-Dioxo-thiazolidine mit narkotischen Eigenschaften (1937)

Erlenmeyer, H. ; von Meyenburg, Harald

New York, NY : Wiley-Blackwell

Helvetica Chimica Acta 20 (1937), S. 1388-1393

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Schlagwort(e): Chemistry ; Organic Chemistry

Quelle: Wiley InterScience Backfile Collection 1832-2000

Thema: Chemie und Pharmazie

Materialart: Digitale Medien

URL: http://dx.doi.org/10.1002/hlca.193702001186

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