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  • Organic Chemistry  (354)
  • Inorganic Chemistry  (161)
  • Life and Medical Sciences  (88)
  • Aircraft Propulsion and Power  (38)
  • Aircraft Design, Testing and Performance  (23)
  • Aircraft Stability and Control  (18)
  • 1945-1949  (682)
  • 1948  (682)
Collection
Keywords
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Years
  • 1945-1949  (682)
Year
  • 1
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    Determination of Aircraft Antenna Loads Produced by Natural Icing Conditions (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight investigation was made to determine the effect of distance flown in the icing region, antenna length, and antenna angle on the tension occurring in aircraft antennae while in regions of aircraft icing. The experimental antennas were of lengths ranging from 15 to 43 feet and were placed at angles of 0 deg to 64 deg with the airplane thrust axis. Distances up to 256 miles were flown in diverse icing conditions at true airspeeds from 157 to 214 miles per hour and pressure altitudes at which icing conditions were encountered. The results indicate that: The effect of ice formation on antenna tension increased with the angle of the antennas with the longitudinal axis of the airplane. The maximum tension for antennae having angles from 0 deg to 15 deg was 68 pounds, whereas the maximum tension for antennas having angles of 44 deg and 64 deg was 274 and 438 pounds, respectively.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E7H26a
    Format: application/pdf
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  • 2
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    The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach Numbers (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NPiCA 6-series airfoils. The experimental results confirm the design expectations in demonstrating for the NACA S-series airfoils either no variation, or an Increase from the low-speed design value, In the lift coefficient at a constant angle of attack with increasing Mach number above the critical. It was not found possible to improve the variation with Mach number of the slope of the lift curve for these airfoils above that for the NACA 6-series airfoils. The drag characteristics of the new airfoils are somewhat inferior to those of the NACA 6- series with respect to divergence with Mach number, but the pitching-moment characteristics are more favorable for the thinner new sections In demonstrating somewhat smaller variations of moment coefficient with both angle of attack and Mach number. The effect on the aero&ynamic characteristics at high Mach numbers of removing the cusp from the trailing-edge regions of two 10-percent-chord-thick NACA 6-series airfoils is determined to be negligible.
    Keywords: Aircraft Stability and Control
    Type: NACA-TN-1771
    Format: application/pdf
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  • 3
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    Extension of Useful Operating Range of Axial-Flow Compressors by Use of Adjustable Stator Blades (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting. The NACA compressor was investigated with three different blade settings: (1) the design blade setting, (2) the stator blades reset for 75 percent of design speed and a load coefficient of 0.48, and (3) the stator blades reset for 75 percent of design speed and a load coefficient of 0.65.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-915 , NACA-ACR-E6E02
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  • 4
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    On the Sound Field of a Rotating Propeller (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The sound field of a rotating propeller is teated theoretically on the basis of aerodynamic principles. For the lower harmonics, the directional characteristics and the radiated sound energy are determined and are in conformity with existing experimental results.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1195 , Physikalische Zeitschrit der Sowjetinion: Physical magazine of the Soviet Union volume 9 number 1; 9; 1; 57-71
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  • 5
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F09b
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  • 6
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine I - Analysis of Turbine Performance (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8A23
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  • 7
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8C17
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  • 8
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    Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Chance Vought XFU-1 Airplane, Ted No. NACA DE 311 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the effects of decreasing the rudder deflection, of decreasing the rudder span, and of differential rudder movements on the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane. The results indicated that decreasing the rudder span or the rudder deflections, individually or jointly, did not seriously alter the spin or recovery characteristics of the model; and recovery by normal use of controls (full rapid rudder reversal followed l/2 to 1 turn later by movement of the stick forward of neutral) remained satisfactory. Linking the original rudders so that the inboard rudder moves from full with the spin to neutral while the outboard rudder moves from neutral to full against the spin will also result in satisfactory spin and recovery characteristics. Calculations of rudder-pedal forces for recovery showed that the expected forces would probably be within the capabilities of a pilot but that it would be advisable to install some type of boost in the control system to insure easy and rapid movement of the rudders.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9H30a
    Format: application/pdf
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  • 9
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    Flight Measurements of the Longitudinal Stability and Control Characteristics of the Grumman F8F-1 Airplane, TED No. NACA 2379 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. These tests were made between February and June of 1947- The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers. The lateral and directional stability and control characteristics of the subject airplane have already been reported (reference 1). Also presented in this paper is a discussion of the normal accelerations induced by yawing velocity and sideslip which were considered ob,jectionable by the pilot for this airplane. A discussion of the undesirable accelerations has been included with a view towards formulating some flying-qualities requirements limiting them.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8H27
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  • 10
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    Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configuration were simulated. The behavior of the model was determined from visual observations, by recording the longitudinal decelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history deceleration curves. It was concluded that the airplane should be ditched at a medium nose-high landing attitude with the landing flaps full down. The airplane will probably make a deep run with heavy spray and may even dive slightly. The fuselage will be damaged and leak substantially but in calm water probably will not flood rapidly. Maximum longitudinal decelerations in a calm-water ditching will be about 4g.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8K18
    Format: application/pdf
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  • 11
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the North American XP-86 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A spin investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the North American XP-86 airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the design gross weight loading. The long-range loading was also investigated and the effects of extending slats and dive flaps were determined. In addition, the investigation included the determination of the size of spin-recovery parachute required for emergency recovery from demonstration spins, the rudder force required to move the rudder for recovery, and the best method for the pilot to escape if it should become necessary to do so during a spin. The results of the investigation indicated that the XP-86 airplane will probably recover satisfactorily from erect and inverted spins for all possible loadings. It was found that fully extending both slats would be beneficial but that extending the dive brakes would cause unsatisfactory recoveries. It was determined that a 10.0-foot-diameter tail parachute with a drag coefficient of 0.7 and with a towline 30.0 feet long attached below the jet exit or a 6.0-foot-diameter wingtip parachute opened on the outer wing tip with a towline 6.0 feet long would insure recoveries from any spins obtainable. The rudder-pedal force necessary to move the rudder for satisfactory recovery was found to be within the physical capabilities of the pilot.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8D22
    Format: application/pdf
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  • 12
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    Preliminary Results of an Investigation by the Wing-Flow Method of the Longitudinal Stability Characteristics of a 1/50-Scale Semispan Model of the McDonnell XP-88 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This paper presents the results of measurements of longitudinal stability of a 1/50-scale model of the XP-88 airplane by the wing-flow method. Lift, rolling-moment, hinge-moment, and pitching-moment characteristics as well as the downwash at the tail were measured over a Mach number range from approximately 0.5 to 1.05 at Reynolds numbers below 1,000,000. No measurements of drag were obtained. No abrupt changes due to Mach number were noted in any of the parameters measured. The data indicated that the wing was subject to early tip stalling; that the tail effectiveness decreased gradually with increasing Mach number up to M = 0.9, but increased again at higher Mach numbers; that the variation of downwash with angle of attack did not change appreciably with Mach number except between 0.95 and 1.0 where d(epsilon)/d(alpha), decreased from 0.46 to 0.32; that at zero lift with a stabilizer setting of -1.5 deg there was a gradually increasing nosing-up tendency with increasing Mach number; and that the control-fixed stability in maneuvers at constant speed gradually increased with increasing Mach number.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8E28A
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  • 13
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    Free-Spinning-Tunnel Tests of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 0.057-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics were determined, as were also the effects of extending the wing slats, of center-of-gravity movement, and-of variation in the mass distribution. The investigation also included wing-tip spin-recovery-parachute tests, pilot-escape tests, and rudder-control-force tests. The investigation indicated that the spin and recovery characteristics of the airplane will be satisfactory for all conditions. It was found that a single 4.24-foot (full-scale) parachute when opened alone from the outboard wing tip or two 8.77-foot (full-scale) parachutes when opened simultaneously, one from each wing tip, would effect satisfactory emergency recoveries (the drag coefficients of the parachutes, based on the surface area of the parachute, were 0.83 and 0.70 for the 4.24- and 8.77-foot parachutes, respectively). The towline length in both cases was 25 feet (full scale). Tests results showed that, if the pilot should have to leave the airplane during a spin, he should jump from the outboard side (left side in a right spin) of the cockpit. The rudder-control force necessary for recovery from a spin was found to be rather high but appeared to be within the upper limits of a pilot's capabilities.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A13
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  • 14
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    Ditching Tests of a 1/20-Scale Model of the Northrop B-35 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds,and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records. Both longitudinal and lateral accelerations were measured. Results are given in tabular form and time-history acceleration curves and sequence photographs are presented. Conclusions based on the model investigation are as follows: 1. The best ditching of the B-35 airplane probably can be made by contacting the water in a near normal landing attitude of about 9 deg with the landing flaps full down so as to have a low horizontal speed. 2. The airplane usually will turn or yaw but the motion will not be violent. The maximum lateral acceleration will be about 2g. 3. If the airplane does not turn or yaw immediately after landing, it probably will trim up and then make a smooth run or porpoise slightly. The maximum longitudinal decelerations that will be encountered are about 6g or 7g. 4. Although the decelerations are not indicated to be especially large, the construction of the airplane is such that extensive damage is to be expected, and it probably will be difficult to find ditching stations where crew members can adequately brace themselves and be reasonably sure of avoiding a large inrush of water.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A29
    Format: application/pdf
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  • 15
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    Ground Tests of a Radial Air-Cooled Engine to Correct a Poor Circumferential Pressure-Recovery Distribution (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of the tests of a power-plant installation to improve the circumferential pressure-recovery distribution at the face of the engine. An underslung "C" cowling was tested with two propellers with full cuffs and with a modification to one set of cuffs. Little improvement was obtained because the base sections of the cuffs were stalled. A set of guide vanes boosted the over-all pressures and helped the pressure recoveries for a few of the cylinders. Making the underslung cowling into a symmetrical "C" cowling evened the pressure distribution; however, no increases in front pressures were obtained. The pressures at the top cylinders remained low and the high pressures at the bottom cylinders were reduced. At higher powers and engine speeds, the symmetrical cowling appeared best from the standpoint of over-all cooling characteristics.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SL7L10
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  • 16
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    Measurements of the Lateral and Directional Stability and Control Characteristics of a P-51H Airplane (AAF No. 44-64164) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flight tests of a P-51H airplane with two different vertical-tail assemblies were made to determine lateral and directional stability and control characteristics. The airplane had satisfactory directional stability in the landing, approach, and wave-off conditions with either tail. In the power-on clean and glide conditions, however, the airplane had weak directional stability with the original tail. The production tail, which had a 7-inch fin extension and a shorter span rudder, improved the directional stability in the power-on clean and glide conditions, but the stability was still weak in the power-on clean condition. Increased altitude in either case caused a slight decrease in the stability. The rudder-trim-force change with speed with either vertical-tail assembly was high. The general aileron control characteristics were satisfactory but the aileron effectiveness failed to meet the Army handling-qualities requirements.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL7L11
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  • 17
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    An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7-by 10-Foot Tunnel: TED No. DE308 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An analysis of the estimated high-speed flying qualities of the Chance Vought XF7U-1 airplane in the Mach number range from 0.40 to 0.91 has been made, based on tests of an 0.08-scale model of this airplane in the Langley high-speed 7- by 10-foot wind tunnel. The analysis indicates longitudinal control-position instability at transonic speeds, but the accompanying trim changes are not large. Control-position maneuvering stability, however, is present for all speeds. Longitudinal lateral control appear adequate, but the damping of the short-period longitudinal and lateral oscillations at high altitudes is poor and may require artificial damping.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8J15-Pt-6
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  • 18
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. II - Operational Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of an axial flow-type turbojet engine with a 4000-pound-thrust rating over a range of pressure altitudes from 5,000 to 50,OOO feet, ram pressure ratios from 1.00 to 1.86, and temperatures from 60 deg to -50 deg F. The low-flow (standard) compressor with which the engine was originally equipped was replaced by a high-flow compressor for part of the investigation. The effects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, acceleration, starting, operation of fuel-control systems, and bearing cooling were investigated. With the low-flow compressor, the engine could be operated at full speed without serious burner unbalance at altitudes up to 50,000 feet. Increasing the altitude and airspeed greatly reduced the operable speed range of the engine by raising the minimum operating speed of the engine. In several runs with the high-flow compressor the maximum engine speed was limited to less than 7600 rpm by combustion blow-out, high tail-pipe temperatures, and compressor stall. Acceleration of the engine was relatively slow and the time required for acceleration increased with altitude. At maximum engine speed a sudden reduction in jet-nozzle area resulted in an immediate increase in thrust. The engine started normally and easily below 20,000 feet with each configuration. The use of a high-voltage ignition system made possible starts at a pressure altitude of 40,000 feet; but on these starts the tail-pipe temperatures were very high, a great deal of fuel burned in and behind the tail-pipe, and acceleration was very slow. Operation of the engine was similar with both fuel regulators except that the modified fuel regulator restricted the fuel flow in such a manner that the acceleration above 6000 rpm was very slow. The bearings did not cool properly at high altitudes and high engine speeds with a low-flow compressor, and bearing cooling was even poorer with a high-flow compressor.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F09a
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  • 19
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    Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects cf control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended. The results indicated that the airplane might not spin at normal spinning-control configuration, but if a spin were obtained, recovery therefrom by full rudder reversal would be satisfactory. It was also indicated that aileron-against settings would lead to violent oscillatory motions and should be avoided.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7L03
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  • 20
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    Effect of First-Stage Blade Design on Performance of Mark 25 Torpedo Power Plant (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The effect of rotor-blade length, inlet angle, and shrouding was investigated with four different nozzles in a single-stage modification of the Mark 25 aerial-torpedo power plant. The results obtained with the five special rotor configurations are compared with those of the standard first-stage rotor with each nozzle. Each nozzle-rotor combination was operated at nominal pressure ratios of 8, 15 (design), and 20 over a range of speeds from 6000 rpm to the design speed of 18,000 rpm. Inlet temperature and pressure conditions of 1OOOo F and 95 pounds per square inch gage, respectively, were maintained constant for all runs.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9G20
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  • 21
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    Longitudinal Stability and Control Characteristics of a B-29 Airplane with a Booster Incorporated in the Elevator Control System to Provide Various Stick-Force and Control-Rate Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The longitudinal stability and control characteristics of a B-29 airplane have been measured with a booster incorporated in the elevator control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in pilots control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L50D11 , Rept-3130
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  • 22
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    Calibration of Air-Flow Meters for J33 Compressor Investigation (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It was determined that over a range of weight flows from 18 to 45 pounds per second the average weight flows measured by the metering device used for the compressor test would be 0.70 percent lower than those measured by the metering device used in the engine tests and the probable variation about this mean would be +/- 0.39 percent. The very close agreement of the metering devices shows that the greater part of the discrepancy in weight flow is attributable to the effect of inlet pressure.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8H03
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  • 23
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    Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. II - Engine Performance (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance characteristics of the X24C-4B turbojet engine over a range of simulated altitudes from 5000 to 45,000 feet,simulated flight Mach numbers from 0 to 1.08, and engine speeds from 4000 to 12,500 rpm. Performance data are presented to show graphically the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. The performance data are generalized to show the applicability of methods used to determine performance at any altitude from data obtained at a given altitude. A complete tabulation of performance data, as well as lubrication- and fuel- system data, is presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE7L26
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  • 24
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    Effect of Turbine Axial Nozzle-Wheel Clearance on Performance of Mark 25 Torpedo Power Plant (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Investigations were made of the turbine from a Mark 25 torpedo to determine the performance of the unit with three different turbine nozzles at various axial nozzle-wheel clearances. Turbine efficiency with a reamed nondivergent nozzle that uses the axial clearance space for gas expansion was little affected by increasing the axial running clearance from 0.030 to 0.150 inch. Turbine efficiency with cast nozzles that expanded the gas inside the nozzle passage was found to be sensitive to increased axial nozzle-wheel clearance. A cast nozzle giving a turbine brake efficiency of 0.525 at an axial running clearance of 0.035 inch gave a brake efficiency of 0.475 when the clearance was increased to 0.095 inch for the same inlet-gas conditions and blade-jet speed ratio. If the basis for computing the isentropic power available to the turbine is the temperature inside the nozzle rather then the temperature in the inlet-gas pipe, an increase in turbine efficiency of about 0.01 is indicated.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8B04
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  • 25
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    Preliminary Results of Nene II Engine Altitude-chamber Performance Investigation (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents the preliminary results obtained using jet nozzle 18.00 inches in diameter, with an area equal to 92.2 percent of the area of the standard jet nozzle for this engine. The experimental results presented are for conditions simulating altitudes from 20,000 to 60,000 feet and ram-pressure ratios from 1.1 to 3.5. These ram-pressure ratios correspond to flight Mach numbers between 0.374 and 1.466. Data obtained with the 18.00 inch-diameter jet nozzle and corrected to standard sea-level conditions showed substantially the same trends with altitude as the data previously obtained with an 18.75-inch-diameter nozzle and with an 18.41-inch-diameter nozzle. Jet thrust, air consumption, and fuel consumption, corrected to standard sea-level conditions, increased rapidly with increasing ram-pressure ratio. In general, corrected net thrust specific fuel consumption increased with increase in ram-pressure ratio. Corrected net thrust decreased with an increase in ram-pressure ratio at an engine speed of 8000 rpm. At corrected engine speeds between 8000 and 10,800 rpm, net thrust first decreased with an increase in ram-pressure ratio and then increased with further increase in ram pressure ratio; at corrected engine speeds above 10,800 rpm, net thrust increased continuously with increase in ram-pressure ratio. Tail-pipe temperature decreased with an increase in ram-pressure ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8H06
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  • 26
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    Preliminary Results of British Nene II Engine Altitude-Chamber Performance Investigation. I - Altitude Performance Using Standard 18.75-Inch-Diameter Jet Nozzle (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the altitude performance characteristics of the British Nene II engine and its components. The present paper presents the preliminary results obtained using a standard jet nozzle. The test results presented are for conditions simulating altitudes from sea level to 60,000 feet and ram pressure ratios from 1.0 to 2.3. These ram pressure ratios correspond to flight Mach numbers between zero and 1.16 assuming a 100 percent ram recovery.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8E12
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  • 27
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    Performance of Compressor XJ-41-V Turbojet Engine I - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings. An initial investigation at an equivalent compressor speed of 8000 rpm was made to determine the performance of the compressor and the collecting chamber and to determine the similarity of the air stream at the entrance to the simulated burner annulus. The mechanical performance of the compressor over a range of actual compressors speeds from 3300 to 8000 rpm is reported.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7A17a
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  • 28
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    Wind-Tunnel Measurements on the Henschel Missile "Zitterrochen" in Subsonic and Supersonic Velocities (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: At the request of the Henschel Aircraft Works. A. G. Berlin. three models of the missile "Zitterrochen" were investigated at subsonic velocities.(open jet 215-millimeter diameter) and at supersonic velocities (open jet 110 by 130 millimeters) in order to determine the effect of various wing forms on the air forces and moments. Three-component measurements were taken, and one model was also investigated with deflected control plates.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1159 , DLUM-3122 , Deutsche Luftfahrtforschung, Untersuchungen und Mitteilungen
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  • 29
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    Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8J12
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  • 30
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    Experimental Pressure Distribution on Fuselage Nose and Pilot Canopy of Supersonic Airplane at Mach Number 1.90 (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the pressure distribution on the fuselage nose and the pilot canopy of a supersonic airplane model has been conducted at a Mach number of 1.90 over a wide range of angles of attack and yaw. Boundary layer separation apparently occurred from the upper surface at angles of attack above 24 degrees and from the lower surface at minus 15 degrees. No separation from the sides of the fuselage was evident at yaw angles up to 12 degrees.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8I07
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  • 31
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    Venturi Tube with Varying Mass Flow (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Measurements on three tubes with flow regulated by suction at the trainling edge of the tube are described. It was possible to vary the mass of air flowing through the tube over a large range. Such tubes could be used for shrouded propellers.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1191 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters; 1945
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  • 32
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A preliminary investigation of an axial-flow gas turbine-propeller engine was conduxted. Performance data were obtained for engine speeds from 8000 to 13,000 rpm and altitudes from 5000 to 35,000 feet and compressor inlet ram pressure ratios from 1.00 to 1.17.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F10
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  • 33
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    Simulated Altitude Performance of Combustor of Westinghouse 19XB-1 Jet-Propulsion Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turbojet engine at various altitudes and engine speeds. The combustion efficiencies and the altitude operational limits were determined; data were also obtained on the character of the combustion, the pressure drop through the combustor, and the combustor-outlet temperature and velocity profiles. At altitudes about 10,000 feet below the operational limits, the flames were yellow and steady and the temperature rise through the combustor increased with fuel-air ratio throughout the range of fuel-air ratios investigated. At altitudes near the operational limits, the flames were blue and flickering and the combustor was sluggish in its response to changes in fuel flow. At these high altitudes, the temperature rise through the combustor increased very slowly as the fuel flow was increased and attained a maximum at a fuel-air ratio much leaner than the over-all stoichiometric; further increases in fuel flow resulted in decreased values of combustor temperature rise and increased resonance until a rich-limit blow-out occurred. The approximate operational ceiling of the engine as determined by the combustor, using AN-F-28, Amendment-3, fuel, was 30,400 feet at a simulated engine speed of 7500 rpm and increased as the engine speed was increased. At an engine speed of 16,000 rpm, the operational ceiling was approximately 48,000 feet. Throughout the range of simulated altitudes and engine speeds investigated, the combustion efficiency increased with increasing engine speed and with decreasing altitude. The combustion efficiency varied from over 99 percent at operating conditions simulating high engine speed and low altitude operation to less than 50 percent at conditions simulating operation at altitudes near the operational limits. The isothermal total pressure drop through the combustor was 1.82 times as great as the inlet dynamic pressure. As expected from theoretical considerations, a straight-line correlation was obtained when the ratio of the combustor total pressure drop to the combustor-inlet dynamic pressure was plotted as a function of the ratio of the combustor-inlet air density to the combustor-outlet gas density. The combustor-outlet temperature profiles were, in general, more uniform for runs in which the temperature rise was low and the combustion efficiency was high. Inspection of the combustor basket after 36 hours of operation showed very little deterioration and no appreciable carbon deposits.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8J29
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  • 34
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    Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Operating characteristics of the 11-stage 4000-pound-thrust axial-flow turbojet engine were determined. A standard compressor and a compressor with the blade angles of the rotor and stator blades increased 5 degrees to obtain greater air flow, were investigated.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F09c
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  • 35
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8B19
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  • 36
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    Free-Spinning, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultke MX-813 (Prototype of XP-92) Airplane as Determined in the Langley 20-Foot Free-Spinning Tunnel (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to evaluate the spin, longitudinal-trim, and tumbling characteristics of a 1/20-scale model of the Consolidated Vultee MX-813 airplane. The effects of control position were determined for the model ballasted to represent the airplane in its design gross weight loading. The model, in general, would not spin but demonstrated a tendency to trim at very high stalled angles of attack. Static tests substantiated the dynamic tests as regards the trim characteristics. Movement of the elevator, however, from up to slightly down was effective in pitching the model from stalled to normal trim attitudes. The model would not tumble.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8G26
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  • 37
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    Tank Tests of a Powered Model of a Compression Plane, NACA Model 171A-2 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed. Lift is obtained from the static pressure of air in the tunnel. In general, the ratio of the gross load to the total resistance increases with increase in load and decrease in speed. This ratio varies between l-7 and 5.7 at high speeds and has a maximum value of 7. The total resistance is nearly the same for both power conditions except at low speeds and heavy loads. No abrupt change in forces on the hull or flow around the hull occurs in. the region of zero draft. The centers of pressure are generally far aft. At the most efficient trim (1.2'), considerable bow-up moment would be required for practicable operation. There is no abrupt transition from the air-borne to the water- borne condition.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8G02
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  • 38
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    Altitude-Wind-Tunnel Investigation of Westinghouse 19B-2 19B-8, and 19XB-1 Jet-Propulsion Engines (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the NACA Cleveland altitude wind tunnel to determine the operational characteristics of the Westinghouse 19B-2, 19B-8, and 19XB-l jet-propulsion engines. The 19B engine is one af the earliest experimental Westinghouse axial flow engines. The 19XB-1 engine is an experimental prototype of the Westinghouse 15 series, having a rated thrust of 1400 pounds. Improvements in performance and operational characteristics have resulted in the 19XB-2B engine with a rated thrust of 1600 pounds. The operational characteristics were determined over a range of simulated altitudes from 5000 to 30,000 feet for the 19B engines and from 5000 to 35000 feet for the 19XB-l engine at airspeed from 20 to 380 miles per hour. The affects of altitude and airspeed on such operating characteristics as operating range, stability of combustion, starting, acceleration, and functioning of the fuel-control system are discussed. Damage to the engines that occurred during the investigation is also briefly discussed. The changes made in the combustion-chamber configuration to improve the operating we are described.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8J28-Pt-1
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  • 39
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    Measurements of the Longitudinal Stability and Control and Stalling Characteristics of a North American P-51H Airplane (AAF No. 4-64164) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of a North American P-51H airplane. The results indicate that the airplane has satisfactory longitudinal stability in all the flight conditions tested at normal loadings up to 25,000 feet altitude. At Mach numbers above 0.7, the elevator push force required for longitudinal trim decreased somewhat because of compressibility effects. The elevator stick force per g in accelerated turns at the forward center-of-gravity position of 24 percent mean aerodynamic chord above 250 miles per hour was in excess of the required limits at both 5,000 and 25,OOO feet altitude. The longitudinal-trim-force changes due to flaps and power were small, but the rudder-trim-force change with power change was high. The stalling characteristics in all the conditions tested were satisfactory.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8B24
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  • 40
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    Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model. Scale-strength bottoms and simulated crumpled bottoms were used to reproduce probable damage to the fuselage. It was concluded that the airplane should be ditched at a landing attitude of about 5 deg with flaps full down. At this attitude, the maximum longitudinal deceleration should not exceed 2g and the landing run will be bout three fuselage lengths. Damage to the fuselage will not be excessive and will be greatest near the point of initial contact with the water.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8E17
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  • 41
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    Summary of Section Data on Trailing-Edge High-Lift Devices (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A summary has been made of available data on the characteristics of airfoil sections with trailing-edge high-lift devices. Data for plain, split, and slotted flaps are collected and analyzed. The effects of each of the variables involved in the design of the various types of flap are examined and, in cases where sufficient data are given, optimum configurations are deduced. Wherever possible, the effects of airfoil section, Reynolds number, and leading-edge roughness are shown. For single and double slotted flaps, where a great mass of unrelated date are available, maximum lift coefficients of a large number of configurations are presented in tables.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L8D09
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  • 42
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    Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet Engines (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by each method were determined. A comparison was also made for a given time of operation of the weight of an augmented engine plus fuel and additional liquids to the weight of a standard engine plus fuel producing the same thrust.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8H11
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  • 43
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    Comparison of Drop and Wind-Tunnel Experiments on Bomb Drag at High Subsonic Speeds (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The drag coefficients of bombs at high velocities velocity of fall was 97 percent of the speed of sound) (the highest are determined by drop tests and compared with measurements taken in the DVL high-speed closed wind tunnel and the open jet at AVA - Gottingen.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1186 , Deutsche Luftfahrtforschung Forschungsbericht; Rept-1570
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  • 44
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    Performance of Allison Model 400-C6 Turbojet-Engine Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The Allison model 400-C6 compressor was operated at an inlet pressure of 12 inches of mercury absolute ana ambient inlet temperature at equivalent impeller speeds of 6000, 7000, and 8500 rpm. Additional runs at an equivalent speed of 7000 rpm and ambient inlet temperature were made at inlet pressures from 7 to 22 inches of mercury absolute. The results of this investigation are compared with those of the 533-A-23 compressors. For the speeds investigated, the Allison model 400-C6 compressor had a maximum adiabatic temperature-rise efficiency of 0.768 at an equivalent speed of 7000 rpm; the corresponding equivalent weight flow was 45.0 pounds per second and the pressure ratio was 1.83. At an equivalent impeller speed of 8500 rpm, the maximum equivalent weight flow was 61.6 pounds per second and the peak pressure ratio of 2.38 occurred at an equivalent weight flow of 52.2 pounds per 1 second and an adiabatic temperature-rise efficiency of 0.714. At an equivalent speed of 7000 rpm, increasing the compressor- inlet pressure increased the maximum equivalent weight flow and the pressure ratio.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8L15
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  • 45
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    Performance of J33-A-23 Turbojet-Engine Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The production-model 333-A-23 turbojet-engine compressor with a 17-blade impeller was operated at ambient and 0 F inlet temperatures and at inlet pressures of 14 and 5 inches mercury absolute for equivalent impeller speeds from 6000 to 12,750 rpm. The results of this investigation are compared with those of the 533-A-21 compressor. At the design equivalent speed of 11,750 rpm the maximum pressure ratio was 4.39. This occurred at the surge point at which the equivalent weight flow was 80.8 pounds per second, ana the adiabatic temperature-rise efficiency was 0.757. The maximum flow at the design equivalent speed was 88.0 pounds per second. The maximum adiabatic temperature-rise efficiency of 0.799 was obtained at an equivalent speed of 10,000 rpm, and equivalent weight flow of 62.9 pounds per second, and a pressure ratio of 3.20. At the maximum equivalent speed investigated (12,750 rpm), a peak pressure ratio of 4.90 was attained at an equivalent weight flow of 85.4 pounds per second and an efficiency of 0.680.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8F15-Pt-1
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  • 46
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    Longitudinal Stability Characteristics of a 1/40-Scale Model of a Proposed Configuration of the XF-91 Airplane Measured by the Wing-Flow Method (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of an investigation in the transonic speed range of the longitudinal stability characteristics of a proposed configuration for the Republic XF-91 airplane. The tests covered a Mach number range of 0.55 to 1.05 and a Reynolds number range from 400,000 to 1,375,000. Lift, pitching-moment, and rolling-moment characteristics of the half model and the hinge moments on the all-moving tail were measured. The downwash factor delta x epsilon / delta x alpha at the tail was determined from the pitching-moment data. A calculation of the elevator deflection and stick force required for trim was also made. It was found that the variation of force and moment coefficients was linear through the test angle-of-attack range of -1 deg to 8 deg at any Mach number; that the stability increased markedly at Mach numbers above 0.85; that the effectiveness of the tail in producing pitching moments decreased about one-third with increasing Mach numbers and that the value of the downwash factor, delta x epsilon / delta x alpha, at the tail decreased from about 0.35 at a Mach number of 0.85 to about zero at a Mach number near 0.95 and became slightly negative at higher Mach numbers. The calculated values of stick force per g and elevator deflection per g, assuming no aerodynamic balance, increased rapidly above a Mach number of 0.85.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8K17
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  • 47
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    Longitudinal Trim and Tumble Characteristics of a 0.057-Scale Model of the Chance Vought XF7U-1 Airplane, TED NO. NACA DE311 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Based on results of longitudinal trim and tumble tests of a 0.057-scale model of the Chance Vought XF7U-1 airplane, the following conclusions regarding the trim and tumble characteristics of the airplane have been drawn: 1. The airplane will not trim at any unusual or uncontrolled angles of attack. 2. The airplane will not tumble with the center of gravity located forward of 24 percent of the mean aerodynamic chord. When the center of gravity is located at 24 percent of the mean aerodynamic chord and slats are extended and elevators are deflected full up, the airplane may tumble if given an external positive pitching moment. 3. The tumbling motion obtained will be readily terminated by deflecting the elevators full down so as to oppose the rotation. 4. The accelerations encountered during an established tumble may be dangerous to the pilot and, therefore, action should be taken to terminate a tumble immediately upon its inception. 5. Simultaneous opening of two wing-tip parachutes having diameters of 4 feet or larger and having drag coefficients of approximately 0.7 will effectively terminate the tumble. 6. Model results indicate that the pilot will not be struck by the airplane if it becomes necessary to leave the airplane during a tumble. The pilot may require aid from an ejection-seat arrangement.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8F14
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  • 48
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    Performance of J-33-A-21 and J-33-A-23 Compressors with and without Water Injection (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: In an investigation of the J-33-A-21 and the J-33-A-23 compressors with and without water injection, it was discovered that the compressors reacted differently to water injection although they were physically similar. An analysis of the effect of water injection on compressor performance and the consequent effect on matching of the compressor and turbine components in the turbojet engine was made. The analysis of component matching is based on a turbine flow function defined as the product of the equivalent weight flow and the reciprocal of the compressor pressure ratio.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8A19
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  • 49
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. Performance of the original and modified engines is compared for a range of simulated flight conditions. The performance data are generalized to show the applicability of methods used to estimate performance at any altitude from data obtained at a given altitude. Engine-windmilling-speed and windmilling-drag data are presented for a range of simulated flight conditions.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8B26 , Rept-928
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  • 50
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    Effect of Inlet Air Distortion on the Steady-State and Surge Characteristics of an Axial-Flow Turbojet Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in an altitude test chamber to determine the effects of inlet airflow distortion on the compressor steady-state and surge characteristics of a high-pressure ratio, axial-flow turbojet engine. Circumferential-type inlet flow distortions were investigated, which covered a range of distortion sector angles from 20 deg to 168 deg and distortion levels up to 22 percent. The presence of inlet airflow distortions at the compressor face resulted in a substantial increase in the local pressure ratio in the distorted region, primarily for the inlet stages. The local pressure ratio in the distorted region for the inlet stages increased as either the distortion sector angle decreased or the percent distortion increased. The average compressor-surge pressure ratio was much more sensitive to inlet airflow distortions at lower engine speeds than at engine speeds near rated. Hence, compressor-surge margin reduction due to inlet airflow distortion was quite severe at the lower engine speeds. Although the average compressor-surge pressure ratio was generally reduced with inlet flow distortion, local pressure ratios across the distorted sector of the compressor were obtained during surge and were significantly greater than the normal compressor-surge pressure ratio. This was a result of increased loading of the inlet stages in the distorted region.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E57L12
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  • 51
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    Investigation of the Stability and Control Characteristics of a 1/10-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley Free-Flight Tunnel, TED No. NACA DE306 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Bureau of Aeronautics, Navy Department, a stability and control investigation of a 1/10-scale model of the Chance Vought XF7U-1 airplane has been conducted in the Langley free-flight tunnel. Results of force end flight tests to determine the power-off stability and control characteristics of the model with slats retracted and extended are presented herein. The longitudinal and lateral stability characteristics were satisfactory for both the slats retracted and extended conditions over the lift range up to the stall. With the slats retracted, the stall was fairly gentle but the model rolled off out of control. With the slats extended, control could be maintained at the stall so that the wings could be kept level even as the model dropped.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8A19
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  • 52
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests. The recovery characteristics of the model were satisfactory for all configurations tested. Spins for the normal control configuration were oscillatory in roll and yaw. Deflecting the leading-edge flaps or the dive brakes did not change the spin and recovery characteristics of the model noticeably. A 10.0-foot tail parachute or a 6.0-foot wing-tip parachute (drag coefficient of 0.75) was found to be effective for recoveries from demonstration spins. The rudder forces in the spin appeared to be within the capabilities of the pilot.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL7L09
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  • 53
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    Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine I - Operational Characteristics and Altitude Limits (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An altitude-test-chamber investigation was conducted to determine the operational characteristics and altitude blow-out limits of a Solar afterburner in a 24C engine. At rated engine speed and maximum permissible turbine-discharge temperature, the altitude limit as determined by combustion blow-out occurred as a band of unstable operation of about 8000 feet altitude in width with maximum altitude limits from 32,000 feet at a Mach number of 0.3 to about 42,000 feet at a Mach number of 1.0. The maximum fuel-air ratio of the afterburner, as limited by maximum permissible turbine-discharge gas temperatures at rated engine speed, varied between 0.0295 and 0.0380 over a range of flight Mach numbers from 0.25 to 1.0 and at altitudes of 20,000 and 30,000 feet. Over this range of operating conditions, the fuel-air ratio at which lean blow-out occurred was from 10 to 19 percent below these maximum fuel-air ratios. Combustion was very smooth and uniform during operation; however, ignition of the burner was very difficult throughout the investigation. A failure of the flame holder after 12 hours and 15 minutes of afterburner operation resulted in termination of the investigation.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8G02
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  • 54
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    Ditching Tests of Two Models of the Army B-36 Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The ditching characteristics of the Army B-36 airplane were determined by testing 1/20- and 1/30-scale dynamic models in calm water in Langley tank no. 2 and at the outdoor catapult. The scope of the tests consisted of ditching the models at various conditions of simulated damage, landing attitudes, and speeds, with various flap settings using several degrees of restraint of the flap hinges. The ditching behavior was evaluated from recordings of deceleration, length of run, and motions of the models. The results showed that the airplane should be ditched at an attitude of about 9 deg with flaps full down. The probable ditching behavior will be a smooth run with a maximum longitudinal deceleration of 3g to 4g and a landing run of 4 to 5 fuselage lengths. Structural failure of the underside of the fuselage will not seriously affect the behavior of the airplane.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8B25
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  • 55
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    Spin Tests of 1/20-Scale Models of the Chance Vought Revised XF6U-1 and F6U-1 Airplanes, TED No. NACA 2390 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on the 1/20-scale model of the Chance Vought XF6U-1 airplane altered to represent the XF6U-1 airplane as it will be spin-tested in flight, and also altered to represent the F6U-1 airplane as it will be produced for service use. Spin tests were made to determine the effects of control settings and movements at the normal loading. The results show that the spins obtained on the revised XF6U-1 airplane will be oscillatory in roll and yaw and that recoveries by rudder reversal will be rapid. Model test results indicate that the F6U-1 airplane will probably not spin. Inasmuch as the results of this investigation show that the new designs are as good as or better than the original XF6U-1 design in regard to spin recovery, it is felt that the conclusions and recommendations reached for the original design can be applied to the new designs for all loading conditions.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL8F03
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  • 56
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    The Influence of the Diameter Ratio on the Characteristics Diagram of the Axial Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: With the further development of axial blowers into highly loaded flow machines, the influence of the diameter ratio upon air output and efficiency gains in significance. Clarification of this matter is important for single-stage axial compressors, and is of still greater importance for multistage ones, and particularly for aircraft power plants. Tests with a single-stage axial blower gave a decrease in the attainable maximum pressure coefficient and optimum efficiency as the diameter ratio increased. The decrease must be ascribed chiefly to the guide surface of the hub and housing between the blades increasing with the diameter ratio.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1125
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  • 57
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    The Influence of Dimensional Modifications upon the Spin and Recovery Characteristics of a Tailless Airplane Model Having Its Wings Swept Forward 15 Deg (Cornelius XFG-1) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free- spinning tunnel scale model of the Cornelius XFG-1 glider, a tailless design having its wings swept forward 15 degrees. It was previously found to possess erratic spin and recovery characteristics, and tests were made to determine modifications which would lead to normal steady spins with consistently good recoveries. The results of the investigation indicated that modifications that aid not appreciably alter the basic design aid not appreciably improve the spin and recovery characteristics. In this instance it appears that the sweptforward wing is the cause of unsatisfactory spin and recovery characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8H17
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  • 58
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    Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: As part of an investigation af the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airplane flight speeds, and altitudes. The maximum load-carrying capacity (available for the nuclear reactor, working fluid, and cargo) of a mercury-turbine powered aircraft would be about half the gross weight of the airplane at a flight speed of 509 miles per hour and an altitude of 30,000 feet. This maximum is obtained with specific condenser frontal areas of 0.0063 square foot per net thrust horsepower with the condenser in a nacelle and 0.0060 square foot per net thrust horsepower with the condenser submerged in the wings (no external condenser drag) for a turbine-inlet pressure of 500 pounds per square inch absolute, a turbine-outlet pressure of 10 pounds per square inch absolute, and 8 turbine-inlet temperature of 1600 F.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8C23 , Rept-952
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  • 59
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    Performance of J33-A-23 Turbojet-Engine Compressor (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The J33-A-23 compressor with a 34-blade impeller was operated at ambient inlet temperature and an inlet pressure of 14 inches mercury absolute over a range of equivalent impeller speeds from 6000 to 11,750 rpm. Additional runs at equivalent speeds of 7,000, 10,000, and 11,750 rpm and ambient inlet temperature were made at inlet pressures of 5 and 10 inches mercury absolute. The results of this investigation are compared with those of the J33-A-23 compressor with a 17-blade impeller. At the design equivalent speed of 11,750 rpm the 533-A-23 compressor with a 34-blade impeller had a peak pressure ratio of 4.49 at an equivalent weight flow of 82.4 pounds per second and an adiabatic temperature-rise efficiency of 0.740. The maximum equivalent flow at design speed was 91.8 pounds per second. The peak efficiency at design speed (0.757) occurred at an equivalent weight flow of 85.5 pounds per second. The maximum adiabatic temperature- rise efficiency of 0.773 was obtained at an equivalent impeller speed of 10,000 rpm, an equivalent weight flow of 65.8 pounds per second, and a pressure ratio of 3.27. At equivalent impeller speeds of.l0,000 and 11,75O rpm a decrease in inlet pressure resulted in a decrease in maximum equivalent weight flow, peak pressure ratio, and peak adiabatic temperature- rise efficiency.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8H13
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  • 60
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms September 10, 1947 to September 15, 1947 at Clinton County Army Air Field, Ohio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The gust and draft velocities from records of NACA instruments installed in P-61C airplanes participating in thunderstorm flights at Clinton County Army Air Field, Ohio, from September 10, 1947 to September 15, 1947, are presented.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L8C31
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  • 61
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    Performance of Compressor of XJ-41-V Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation of the XJ-41-V turbojet-engine compressor was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the original compressor indicated the compressor would not meet the desired engine-design air-flow requirements because of an air-flow restriction in the vaned collector. The compressor air-flow choking point occurred near the entrance to the vaned-collector passage and was instigated by a poor mass-flow distribution at the vane entrance and from relatively large negative angles of attack of the air stream along the entrance edges of the vanes at the outer passage wall and large positive angles of attack at the inner passage wall. As a result of the analysis, a design change of the vaned collector entrance is recommended for improving the maximum flow capacity of the compressor.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE7L12
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  • 62
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    Simulated Altitude Performance of Combustors for the 24C Turbojet Engine. III - Performance of Rectangular-Slot Baskets (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The performance of an annular combustion chamber from a 24C turbojet engine was investigated over a range of simulated altitudes from 20,000 to 55,000 feet and corrected engine rotor speeds from 6000 to 13,000 rpm at a simulated ram-pressure ratio of 1.04. The purpose of the investigation was to determine the effects on the altitude operational limits, combustor-outlet gas temperature distribution, combustion efficiencies, and combustor inlet-to-outlet total-pressure drops of two changes in the 24C-4B basket air-passage arrangements that were designed to improve combustor-outlet temperature distribution. These changes were: (a) replacement of the downstream secondary air holes with large rectangular slots further upstream (rectangular-slot basket), and (b) enlargement of anticoking holes in the rectangular-slot basket (modified rectangular-slot basket). The results indicate that improved outlet-gas temperature distribution of each succeeding combustor basket investigated was attained at a sacrifice in the altitude limit of operation. The altitude limits of operation of the combustor with the original basket ranged from 34,000 feet at a corrected engine speed of 6000 rpm to a maximum of 52,000 feet at 12 ' 500 rpm. The altitude limits of the rectangular-slot basket were about 2000 feet lower throughout the engine speed range than those of the original basket. The altitude limits of the combustor with the modified rectangular-slot basket were about equivalent to those of the other baskets in the corrected-engine-speed range from 12,000 to 12,500 rpm but were about 10,000 feet lower than those of the original basket in the corrected-engine-speed range from 6000 to 9000 rpm. For the same inlet-air conditions, the combustion efficiencies were highest for the original basket and progressively lower for each of the other two baskets. The combustor inlet-to-outlet pressure drops of all three combustor baskets at the same operating conditions were within +/- 10 percent of the pressure drop of the original basket.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8G13
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  • 63
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    Investigation of X24C-2 10-Stage Axial-Flow Compressor. III - Surge Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Compressor operation at low air flows for a given speed is limited by unstable flow conditions, commonly called surge. An investigation of surge in centrifugal compressors (reference 1) showed that the pulsation of pressures and velocities occurred when the slope of the compressor characteristic curve was positive and that the magnitude and frequency, as well as the incidence of surge, depended on the capacity and resistance of the total system. Although the theory presented in reference 1 is applicable to axial-floe compressors, little experimental information is available on the surge characteristics of the individual stages of axial-flow compressors, or on the variation of the surge characteristics with operating conditions. During the investigation to determine the performance of the X24C-2 compressor (references 2 and 3), instrumentation was added to study the surge characteristics and to determine the effect of speed and inlet pressure on the frequency, amplitude, and phase relation of the pressure pulsations behind each stage.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8H06
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  • 64
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    Performance of Compressor of XJ-41-V Turbojet Engine V-Performance Analysis of Compressor with Revised Vaned Collector over Range of Compressor Speeds from 3600 to 11,500 RPM (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation of the XJ-41-V turbojet-engine compressor with a revised vaned collector was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal compressors of this type. The original vaned collector was revised by increasing the flow area at the vaned collector entrance. A maximum adiabatic efficiency of 0.81 was obtained et a corrected weight flow of 36.5 pounds per second and a pressure ratio of 1.90. The peak pressure ratio was 3.93 and occurred at an impeller speed of 11,500 rpm at a corrected weight flow of 65.5 pounds per second. Revision of the vaned collector resulted in an increased airflow capacity over the speed range. The design air-flow capacity of 78 pounds per second was very nearly reached at the engine design speed of 11,500 rpm. The compressor air-flow choking point occurred in the vaned collector passage; however, at speeds above 8300 rpm, the air-flow capacity of the impeller was being approached as indicated by large pressure losses in the impeller at maximum air-flow conditions. An increase in compressor air-flow capacity at the higher speeds can possibly be obtained 5y removal of the flow restriction in the impeller, which would result in an increased air density at the vaned collector entrance.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SE8A22
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  • 65
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine II-Analysis of Compressor Performance (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8A26a
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  • 66
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel. The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8C16a
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  • 67
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Wind tunnel investigations were performed to determine the performance properties of an axial-flow gas turbine-propeller engine II. Windmilling characteristics were determined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F10a
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  • 68
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    Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemeters and a Doppler velocimeter radar unit. The results of this investigation indicated no unusual variation in the lateral acceleration characteristics. After the cessation of powered flight, the lateral oscillation quickly damped to zero. The data indicated that the airplane, at low lift coefficients, should not experience any abrupt trim changes until it attains a Mach number of 0.97. The change in normal-force coefficient associated with this trim change will amount to about 0.03 with the center of gravity located at 4.48% of the mean aerodynamic chord. At higher lift coefficients, on the basis of other data, the Mach number at which this trim change occurs would be expected to be decreased. The neutral point of the model at Mach numbers near 1.05 was estimated to fall at 45% of the mean aerodynamic chord, assuming a lift-curve slope of 0.05. A value of the static-directional-stability parameter dCn/d(psi) of approximately -0.002 was estimated for a Mach number of 0.93. The values of drag coefficient obtained from both model flights were in a good comparative agreement. The highest drag coefficient occurred at a Mach number of 1.01 and was equal to 0.044.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L8G29
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  • 69
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    Performance Investigations of a Large Centrifugal Compressor from an Experimental Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted on a large centrifugal compressor from an experimental turbojet engine to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the compressor indicated that the compressor would not meet the desired engine-design air-flow requirements (78 lb/sec) because of an air-flow restriction in the vaned collector (diffuser). Revision of the vaned collector resulted in an increased air-flow capacity over the speed range and showed improved matching of the impeller and diffuser components. At maximum flow, the original compressor utilized approximately 90 percent of the available geometric throat area at the vaned-collector inlet and the revised compressor utilized approximately 94 percent, regardless of impeller speed. The ratio of the maximum weight flows of the revised and original compressors were less than the ratio of effective critical throat areas of the two compressors because of the large pressure losses in the impeller near the impeller inelt and the difference increased with an increase in impeller speed. In order to further increase the pressure ratio and maximum weight flow of the compressor, the impeller must be modified to eliminate the pressure losses therein.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8H13
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  • 70
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    Effect of Distribution of Basket-Hole Area on Simulated Altitude Performance of 25 1/2-Inch-Diameter Annular-Type Turbojet Combustor (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A simulated altitude performance of a 25 1/2-inch-diameter annular-type turbojet combustor was performed to determine the effect of the distribution of basket-hole area on the altitude operational limits of the engine as imposed by the combustor.Total pressure drop was recorded, as well as the effect of fuel-nozzle flow capacity,and fuel-nozzle spray angle for one basket configuration. General observations were made for all configurations regarding flames, extent of afterburning, and durability of the baskets.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8A02
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  • 71
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures were evaluated.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8B19a
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  • 72
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-foot Wind Tunnel. Force and Moment Tests (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of the McDonnell XP-85 airplane were conducted to determine its longitudinal, lateral, and directional stability and the characteristics of the aileron, the ruddervator, the leading-edge droop nose flap, and the stall control vanes. The directional stability of the airplane with numerous skyhook modifications and with a ventral fin was also investigated. The results of the tests showed that the effectiveness of the droop nose flaps and the stall control vanes was negligible with regard to either the maximum lift or longitudinal stability of the airplane. Contrary to any previous small-scale results, extension of the skyhook caused a 75-percent reduction in the directional stability of the airplane for both low and high values of lift coefficient. The simplest solution to the problem short of a major redesign of the skyhook appears to be the adoption of a ventral fin.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA8I23
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  • 73
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    Preliminary Results of Nene II Engine Altitude-chamber Performance Investigation (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents preliminary results obtained using a jet nozzle of 18.41 inches in diameter, giving an area equal to 96.4 percent of the area of the standard jet nozzle of this engine. The test results presented are for conditions simulating altitudes from seal level to 50,000 feet and ram-pressure ratios from 1.00 to 2.70. The ram pressure ratios correspond to flight Mach numbers between zero and 1.28.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F14
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  • 74
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    Performance of Compressor of XJ-41-V Turbojet Engine II - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 rpm (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Air Material Command, Army Air Forces, an investigation was conducted by the NACA Cleveland laboratory to determine the performance characteristics of the compressor of the XJ-41-V turbojet engine. This report is the second in a series presenting the compressor performance and analysis of flow conditions in the compressor. The static-pressure variation in the direction of flow through the compressor and the location and the cause of the maximum flow restriction at an equivalent speed of 8000 rpm are presented. After the initial runs were reported, the leading edges of the impeller blades and the diffuser surfaces were found to have been roughened by steel particles from a minor failure of auxiliary equipment. The leading edges of the impeller blades were refinished and all high spots resulting from scratches in the diffuser and the accessible parts of the vaned collector passages were removed. The initial overall performance and that obtained with the refinished blades are presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7E05
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    Performance of Compressor of XJ-41-V Turbojet Engine VI - Analysis of Compressor Flow Choking (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-v turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow area was utilized in the original compressor and 94percent in the revised com$ressor. The increase in maximum weight flow obtained with the revised compressor was disproportionate to the increased effective critical throat area because. the air density at the revised vaned-collector entrance for maximum flow was lower than that obtained in the original compressor. This reduction in density resulted from the large pressure losses near the impeller inlet of the revised compressor, which is indicative of impending flow choking in the impeller, The.calculated maximum corrected weight-flow capacity of a compressor consisting of the revised vaneless diffuser and vaned collector with a theoretical impeller that combined peak impeller pressure ratio and peak impeller efficiency at the . maximum flow point would be 112 pounds per second for an equivalent impeller speed of 11,500 rpm;
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE8C12
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  • 76
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    Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98 at an equivalent weight flow of 73.4 pounds per second and an adiabatic temperature-rise , efficiency of 0.701. When the compressor speed was reduced from the design speed to 6000 rpm, the adiabatic temperature-rise efficiency increased to 0.747. At the maximum equivalent speed investigated (13,400 rpm), a peak pressure ratio of 5.09 was obtained at an adiabatic temperature-rise efficiency of 0.617 and an equivalent weight flow of 66.O pounds per second. An increase in inlet pressure from 5.5 to 14 inches mercury absolute, with a consequent increase in Reynolds number index, improved the pressure ratio but had no apparent effect on the ratio of temperature rise through the compressor to inlet temperature. The variation of the peak adiabatic temperature-rise efficiency with inlet pressure is in the direction that would be expected from a Reynolds number effect. Decrease in the inlet temperature from 80 to -40 F, with a consequent increase in Reynolds number index, resulted in scatter of the pressure-ratio data and increased values of temperature ratio. The variation of the adiabatic temperature-rise efficiency with inlet temperature is probably the result of heat-transfer effects and scatter in the pressure ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SE8C15
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  • 77
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: As part of an investigation of the performance and operational characteristics of the axial-flow gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100 R. The highest compressor pressure ratio obtained was 6.15 at a corrected air flow of 23.7 pounds per second and a corrected turbine-inlet temperature of 2475 R. Peak adiabatic compressor efficiencies of about 77 percent were obtained near the value of corrected air flow corresponding to a corrected engine speed of 13,000 rpm. This maximum efficiency may be somewhat low, however, because of dirt accumulations on the compressor blades. A maximum adiabatic turbine efficiency of 81.5 percent was obtained at rated engine speed for all altitudes and turbine-inlet temperatures investigated.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8F10c
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  • 78
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Performance properties and operational characteristics of an axial-flow gas turbine-propeller engine were determined. Data are presented for a range of simulated altitudes from 5,000 to 35,0000 feet, compressor inlet- ram pressure ratios from 1.00 to 1.17, and engine speeds from 8000 to 13,000 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E8F10b
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  • 79
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    Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1176 , Untersuchungen und Mitteilungen; 1023/5
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  • 80
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    Phasenuntersuchungen im System Vanadin-Sauerstoff und die Krystallstruktur von V12O26 (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 8-21 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Das System Vanadin - Sauerstoff wurde zwischen VO2 und V2O5 einer erneuten Prüfung unterzogen. Mit Hilfe von Pulver- und Einkrystallaufnahmen wurde ein Oxyd der Zusammensetzung V02,17 aufgefunden. Seine Krystallstruktur wurde durch ausschliessliche Verwendung von Fouriermethoden vollständig bestimmt. Die Elementarzelle ist monoklin und hat die Dimensionen a = 11,90Å, b = 3,67Å c = 10,12Å und,β = 100°52′. Der Zellinhalt entspricht der Formel V12O26. Die Raumgruppe ist C32h—C 2/m. Jedes Vanadinatom ist oktaedrisch von Sauerstoff umgeben. Die einzelnen Oktaeder sind teils durch gemeinsame Ecken, teils durch gemeinsame Kanten verknüpft.
    Additional Material: 5 Ill.
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    URL: http://dx.doi.org/10.1002/hlca.19480310104
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  • 81
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    Über 5-Chloracetyl-thiazol (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 26-28 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310106
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  • 82
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    Beiträge zu dem Problem der Ähnlichkeit in der Chemie I (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 32-40 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310109
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  • 83
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    Zur Kenntnis des 5-Aminocumarons (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 75-77 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Additional Material: 1 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310114
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  • 84
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    Zur Kenntnis des Kohlenstoffringes. 45. Mitteilung. Über die Gültigkeitsgrenze der Bredt' schen Regel bei bicyclischen Verbindungen mit einem vielgliedrigen Ring (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 92-97 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310119
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  • 85
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    Recherches sur l'amidon XXXVI. La Perméthylation de la lichénine (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 100-103 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310121
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  • 86
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    Recherches sur l'amidon XXXIX. L'amylose de maïs (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 108-110 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310124
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  • 87
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    Etudes sur les matières végétales volatiles LVIII. Synthèse de l'acide α, α, β-triméthylsubérique (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 151-156 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Les synthèses de l'ester et de l'acide α,α,β-triméthylsubériques ont été effectuées en vne de celle de la triméthyl-1 1. 2-cycloheptanone-7 et. au delà, de l'irone telle qu'elle a été formu1ée par Ruzicka, et de produits apparentés.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310132
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  • 88
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    Sur la production de l'ozone par l'électrolyse des solutions aqueuses d'acide fluorhydrique (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 172-176 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: L'électrolyse des solutions aqueuses d'acide fluorhydrique trés concentré a été effectude à la fempérature de - 15° dam un appareil approprié; elle donne lieu, à l'anode, à la production d'une petite quantité d'ozone qui a été décelée par le spectre d'absorption ultraviolet caractéristique de ce corps et analysée par la méthode de dosage ordinnire. Le gaz anodique ne renfermait pas d'autres corps que l'oxygéne et l'ozone.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/hlca.19480310136
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  • 89
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    Über Steroide. 76. Mitteilung. Monodehydro-marrianol- und -doisynolsäure. Über oestrogene Carbonsäuren XXIII (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 229-236 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310143
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  • 90
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    Glucoside und β-1,3,4,6-Tetraacetyl-glucose aus Triacetyl-glucosan-α〈1,2〉β〈1,5〉 (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 281-286 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310148
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  • 91
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    Über Steroide und Sexualhormone. 148. Mitteilung. Synthese des 14-Allo-17-iso-progesterons (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 249-256 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310146
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  • 92
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    Le dosage semi-quantitatif de l'ion sulfurique (SO4″) dans les eaux naturelles (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 290-292 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Additional Material: 1 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310150
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  • 93
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    Komplexone VII. Titration von Metallen mit Nitrilotriessigsäure H3X. Endpunktsindikation durch pH-Effekte (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 331-340 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Es werden zwei Methoden zur Titration von: Al, Ca, C, d, Ce, Co, Cu, Fe(II), Hg(II), La, Mn, Mg, Ni, Pb und Zn angegeben, welche mit einer Genauigkeit von mindestens 1 % arbeiten und auch für recht verdünnte Lösungen anwendbar sind. Arbeitsvorschriften siehe S. 334 und 338.
    Additional Material: 5 Ill.
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    URL: http://dx.doi.org/10.1002/hlca.19480310204
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  • 94
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    Asymmetrischer Abbau von D, L-Methionin. durch Hefe (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 352-354 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310206
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  • 95
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    Etudes sur les matières végétales volatiles LX. Présence d'époxydihydrocaryophyllène (Caryophyllenoxyd de Treibs) dans l'extrait benzénique de bourgeons floraux du giroflier (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 378-381 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: L'extrait obtenu en traitant les bourgeons floraux du giroflier par le benzène ne renferme pas de caryophyllkne mais bien de l'époxy-dihydrocaryophyllèe(Caryophyllenoxyd de Treibs), tandis que le tourteau lime, sous l'action de l'eau bouillante, une huile essentielle constituée en majeure partie de caryophyllène. Ce dernier n'est donc pas un produit biologique.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310210
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  • 96
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    Die Aktivität der Lipase und der Cholinesterase bei fettfreier Diät und bei E-Avitaminose. 5. Mitteilung über das Verhalten der essentiellen Fettsäuren im Tierkörper (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 381-386 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Es wird der Lipase- und Cholinesteresegehalt im Plasma von fettfrei ernährten männlichen Ratten untersucht. Dabei zeigt sich, dass bei völligem Fettentzug die Lipaseaktivität (gemessen an der Tributyrinspaltung) gegenüber der Norm stark herabgesetzt ist.
    Additional Material: 2 Tab.
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    URL: http://dx.doi.org/10.1002/hlca.19480310211
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  • 97
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    Etudes sur les matières végétales volatiles LXI. Présence de nérolidol dans les huiles essentielles de papilionacées. 3ème communication (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 408-417 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Le bois de Myroroxylon Pereirae(Royle) Klotzsch, arbre dont on obtient le baume du Pérou, renferme une huile essentielle qui est constituée en majeure partie par du nérolidol, accompagné de cadinènes et d'un l-cadinol, tandis que le bois d'especes voisines (Myrocarpus frondosus et M. fastigiatus Allem. ou cabreuva) renferme du nérolidol, du l-cadinol et du bisabolol. L'écorce (liège) ne renferme pas de nérolidol. L'exploitation des arbres épuisds par la production du baume doit ênvisagée en vue de l'obtention de nérolidol.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/hlca.19480310217
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  • 98
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    Komplexone VIII. Titration von Metallen mit Uramidiessig'säure H3Z. Endpunktsindikation durch pH-effekte (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 456-459 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Es werden zwei Titrationsmethoden zur Bestimmung von Ca, Ce, Co, La, Mg, Mn, Ni, Zn und A1 angegeben, die rnit Uramildiessigsäure arbeiten. Einzig bei Mg besitzen diese Methoden einen Vorteil gegenüber denjenigen rnit Nitrilotriessigsäure.
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    URL: http://dx.doi.org/10.1002/hlca.19480310222
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  • 99
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    Strychnos-Alkaloide. 7. Mitteilung. Über die Oxydation von Strychnin mit Kaliumpermanganat in schwach saurer Lösung (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 505-513 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Oxydation von Strychnin mit Kaliumpermanganat in schwach saurer wässeriger Lösung wurde ein bisher unbekanntes Oxydationsprodukt C21H22O4N2 erhalten. Aus dem chemischen Ver halten konnte für das letztere die Konstitution eines 8-Oxy-15oxo-8,15-dihydro-strychnins (IIIa) abgeleitet werden.
    Additional Material: 1 Ill.
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    URL: http://dx.doi.org/10.1002/hlca.19480310230
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  • 100
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    Synthèses de produits macrocycliques à odeur musquée. 8e communication Synthèse de la civettone naturelle (1948)
    New York, NY : Wiley-Blackwell
    Helvetica Chimica Acta 31 (1948), S. 543-553 
    Details
    ISSN: 0018-019X
    Keywords: Chemistry ; Organic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1° L'èhylPne-cètal du cèto-9-heptadècane-dioate d'éthyle a été cyelisé en l'éthylène-cétal de la céto-9-cyclo-heptadécanol-1-one-17. Cette dernière a été réduite catalytiquement en l'éthy1ène-cétal des deux céto-9-cyclo-heptadécane-diol-l,17 diastéreoméres. Ceux-ci furent transformés en les deux bromo-aeétates correspondants qui donnèrent, par réduction au zinc, un mélange de civettone trans et de civettone cis.
    Additional Material: 1 Tab.
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    URL: http://dx.doi.org/10.1002/hlca.19480310234
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