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 Decade: 1940-1949
 Year: 1947
 Month: April
 Collection: National Advisory Committee for Aeronautics Collection
Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Date: April 24, 1947
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Date: April 8, 1947
Creator: Foster, Gerald V.
Description: The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack. The horizontal-tail surveys were made over a fairly wide range of angles of attack at zero degrees yaw. Several power and flap conditions were investigated. The results are presented in the form a dynamic pressure ratios, sidewash angles, and downwash angles plotted against vertical distance from the fuselage center line. The results of the investigation indicate that a vertical tail located in a conventional position would be in a field of flow where the dynamic pressure ratios at the horizontal tail to be increased; for equal lift coefficients, the effect of power or flap deflection on the direction of flow at any particular point in the region of the horizontal tail is small.
Contributing Partner: UNT Libraries Government Documents Department
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines, 4, Analysis of Compressor Performance

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines, 4, Analysis of Compressor Performance

Date: April 4, 1947
Creator: Dietz, Robert O.
Description: Investigations were conducted in the Cleveland altitude wind tunnel to determine the performance and operational characteristics of the 19B-2, 19B-8, and 19XS-1 turbojet engines. One objective was to determine the effect of altitude, flight Mach number, and tail-pipe-nozzle area on the performance characteristics of the six-stage and ten-stage axial-flow compressors of the 19B-8 and 19XB-1 engines, respectively, The data were obtained over a range of simulated altitudes and flight Mach numbers. At each simulated flight condition the engine was run over its full operable range of speeds. Performance characteristics of the 19B-8 and 19XB-1 compressors for the range of operation obtainable in the turboJet-engine installation are presented. Compressor characteristics are presented as functions of air flow corrected to sea-level conditions, compressor Mach number, and compressor load coefficient. For the range of compressor operation investigated, changes in Reynolds number had no measurable effect on the relations among compressor Mach number, corrected air flow, compressor load coefficient, compressor pressure ratio, and compressor efficiency. The operating lines for the 19B-8 compressor lay on the low-air-flow side of the region of maximum compressor efficiency; the 19B-8 compressor operated at higher average pressure coefficients per stage and produced a lower over-all pressure ratio than did ...
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine

Date: April 1, 1947
Creator: Stanitz, John D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Application of an ultraviolet spectrophotometric method to the estimation of alkylnaphthalenes in 10 experimental jet-propulsion fuels

Date: April 30, 1947
Creator: Cleaves, Alden P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The application of high-temperature strain gauges to the measurements of vibratory stresses in gas-turbine buckets

The application of high-temperature strain gauges to the measurements of vibratory stresses in gas-turbine buckets

Date: April 1, 1947
Creator: Kemp, R H
Description: The feasibility of measuring the vibration in the buckets of a gas turbine under service conditions of speed and temperature was determined by use of a high temperature wire strain gauge cemented to a modified supercharger turbine bucket. A high-temperature wire strain gauge and the auxiliary mechanical and electrical equipment developed for the investigation are described.
Contributing Partner: UNT Libraries Government Documents Department
An application of statistical data in the development of gust-load criterions

An application of statistical data in the development of gust-load criterions

Date: April 1, 1947
Creator: Bland, Reginald B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Axial-flow fan and compressor blade design data on 52.5 degrees stagger and further verification of cascade data by rotor tests

Axial-flow fan and compressor blade design data on 52.5 degrees stagger and further verification of cascade data by rotor tests

Date: April 1, 1947
Creator: Bogdonoff, Seymour M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds

The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds

Date: April 23, 1947
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Canopy loads investigation for the F6F-3 airplane

Canopy loads investigation for the F6F-3 airplane

Date: April 14, 1947
Creator: Cocke, Bennie W , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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