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  • Inorganic Chemistry  (578)
  • Polymer and Materials Science  (440)
  • Aircraft Propulsion and Power  (126)
  • Aircraft Stability and Control  (76)
  • 1945-1949  (1,220)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11c
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to -metal heat transfer coefficient, and of the effect of changing the thermal conductivity of the blade metal for a constant cross sectional area blade with two quarter inch diameter coolant passages.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11F
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of 10-Stage Axial-Flow X24C-2 Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7G11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of Wind-Tunnel Predictions with Flight Measurements of the Longitudinal-Stability and -Control Characteristics of a Douglas BTD-1 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Low Mach number longitudinal-stability and control characteristics as predicted by use of wind tunnel data from a powered 3/16-scale model are compared with flight test measurements of a Navy BTD-1 airplane. The accuracy of the wind tunnel data and the discrepancies involved in attempting to correlate with flight data are discussed and analyzed. The comparison showed that wind tunnel predictions were, in general, in good agreement with flight test data. The predicted values were for the most part sufficiently accurate to show the satisfactory and unsatisfactory characteristics in the preliminary design stage and to indicate possible methods of improvement. The discrepancies which did occur were attributed principally to physical dissimilarities between model and airplane and the instability to determine accurately the flight power conditions. The effect of Mach number was considered negligible since the maximum flight test value was about 0.5. In order to simulate more closely the flight conditions and hence obtain more accurate data for predictions, it appears desirable to perform large-scale tests of unorthodox control surfaces such as the sealed vaned elevators with which the airplane was equipped.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A6L30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Temperatures and Stresses on Hollow Blades For Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1183 , Forschungsbericht-1879 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters Berlin-Adlershof
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Computed Temperature Distribution and Cooling of Solid Gas-Turbine Blades (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Computations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F).
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11h
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Investigation of X24C-2 10-Stage Axial-Flow Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Compressor from the X24C-2 turbojet engine was evaluated. Speeds of 80, 89, and 100 percent of equivalent design speed with inlet-air pressures of 6 and 12 inches of mercury absolute and inlet-air temperaures of approximately 538 degrees, 459 degrees,and 419 degrees R ( 79 degrees, 0 degrees, and minus 40 degrees F). Results were compared with prior investigations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7H22
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability and Control Specification except for excessive elevator control forces in maneuvering flight and the inadequacy of the longitudinal trimming control at low airspeeds.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A7G01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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