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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Restricted Report
 Collection: Technical Report Archive and Image Library
Kinetic temperature of wet surfaces : a method of calculating the amount of alcohol required to prevent ice, and the derivation of the psychometric equation

Kinetic temperature of wet surfaces : a method of calculating the amount of alcohol required to prevent ice, and the derivation of the psychometric equation

Date: January 1, 1953
Creator: Hardy, J K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance Charts for a Turbojet System

Performance Charts for a Turbojet System

Date: June 1, 1947
Creator: Karp, Irving M.
Description: Convenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion-chamber-outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge-nozzle coefficient, losses in total pressure in the inlet to the jet-propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion-chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion-chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests and analysis of three 10-foot-diameter three-blade tractor propellers differing in pitch distribution

Wind-tunnel tests and analysis of three 10-foot-diameter three-blade tractor propellers differing in pitch distribution

Date: August 1, 1946
Creator: Gilman, Jean, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

A correlation of loadings and afterbody length-beam ratios of various flying-boat hulls

Date: June 1, 1946
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine II

A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine II

Date: June 1, 1946
Creator: Evvard, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Progress report on strength and creep of special ceramic bodies in tension at elevated temperatures

Progress report on strength and creep of special ceramic bodies in tension at elevated temperatures

Date: June 1, 1946
Creator: Burdick, M D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column and plate compressive strengths of aircraft structural materials : extruded 14S-T aluminum alloy

Column and plate compressive strengths of aircraft structural materials : extruded 14S-T aluminum alloy

Date: May 1, 1946
Creator: Niles, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Charts for critical combinations of longitudinal and transverse direct stress for flat rectangular plates

Date: March 1, 1946
Creator: Stein, Manuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of tail and wing-tip spin-recovery parachutes as determined by tests in the Langley 20-foot free-spinning tunnel

Comparison of tail and wing-tip spin-recovery parachutes as determined by tests in the Langley 20-foot free-spinning tunnel

Date: March 1, 1946
Creator: Malvestuto, Frank S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Date: March 1, 1946
Creator: Koven, William & Kayten, Gerald G.
Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudder-fixed and rudder-free static directional stability was good. Hinge moment obtained at zero sideslip was satisfactory for determining aileron forces in sideslip.
Contributing Partner: UNT Libraries Government Documents Department
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