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 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
Critical combinations of longitudinal and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Critical combinations of longitudinal and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Date: March 1, 1946
Creator: Libove, Charles
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of towline tension and stability of spin-recovery parachutes

Determination of towline tension and stability of spin-recovery parachutes

Date: March 1, 1946
Creator: Wood, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of rotor-tip speed on helicopter hovering performance and maximum forward speed

Effect of rotor-tip speed on helicopter hovering performance and maximum forward speed

Date: March 1, 1946
Creator: Gessow, Alfred
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Knock-Limited Performance of Fuel Blends Containing Aromatics V : N-Propylbenzene, N-Butylbenzene, Isobutylbenzene, M-Xylene, and 1-Isopropyl-4-Methylbenzene

The Knock-Limited Performance of Fuel Blends Containing Aromatics V : N-Propylbenzene, N-Butylbenzene, Isobutylbenzene, M-Xylene, and 1-Isopropyl-4-Methylbenzene

Date: March 1, 1946
Creator: Meyer, Carl L. & Branstetter, J. Robert
Description: Results are reported of knock-limited tests of five aromatics, each individually blended with selected base fuels and tested with and without TEL, using 17.6, F-4, and F-3 small-scale engines. The five aromatics rated in the following order of decreasing antiknock effectiveness at fuel/air ratio 0.10: m-xylene, 1-isopropyl-4-methylbenzene, n-propylbenzene, isobutylbenzene, and n-butylbenzene.
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft-engine cylinder III : four aromatics, six ethers

Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft-engine cylinder III : four aromatics, six ethers

Date: March 1, 1946
Creator: Jonash, Edmund R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited performance tests of 2, 2, 3, 4-tetramethylpentane, 2, 3, 3, 4-tetramethylpentane, 3, 4, 4-trimethyl-2-pentane, and 2, 3, 4-trimethyl-2-pentane in small-scale and full-scale cylinders

Knock-limited performance tests of 2, 2, 3, 4-tetramethylpentane, 2, 3, 3, 4-tetramethylpentane, 3, 4, 4-trimethyl-2-pentane, and 2, 3, 4-trimethyl-2-pentane in small-scale and full-scale cylinders

Date: March 1, 1946
Creator: Branstetter, J Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Test-stand investigation of cooling characteristics and factors affecting temperature distribution of a double-row aircraft engine

Test-stand investigation of cooling characteristics and factors affecting temperature distribution of a double-row aircraft engine

Date: March 1, 1946
Creator: Jones, Robert J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of induced velocity in front of an inclined propeller by a magnetic-analogy method

Determination of induced velocity in front of an inclined propeller by a magnetic-analogy method

Date: February 1, 1946
Creator: Lahatte, James A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Measurements to Determine Effect of a Spring-Loaded Tab on Longitudinal Stability of an Airplane

Flight Measurements to Determine Effect of a Spring-Loaded Tab on Longitudinal Stability of an Airplane

Date: February 1, 1946
Creator: Hunter, Paul A. & Reeder, John P.
Description: In conjunction with a program of research on the general problem of stability of airplanes in the climbing condition, tests have been made of a spring-loaded tb which. is referred to as a ?springy tab,? installed on the elevator of a low-wing scout bomber. The tab was arranged to deflect upward with decrease in speed which caused an increase in the pull force required to trim at low speeds and thereby increased the stick-free static longitudinal stability of the airplane. It was found that the springy tab would increase the stick-free stability in all flight conditions, would reduce the danger of inadvertent stalling because of the definite pull force required to stall the airplane with power on, would reduce the effect of center-of-gravity position on stick-free static stability, and would have little effect on the elevator stick forces in accelerated f11ght. Another advantage of the springy tab is that it might be used to provide almost any desired variation of elevator stick force with speed by adjusting the tab hinge-moment characteristics and the variation of spring moment with tab deflection. Unlike the bungee and the bobweight, the springy tab would provide stick-free static stability without requiring a pull force to ...
Contributing Partner: UNT Libraries Government Documents Department
JRM-1 landing impact characteristics from model tests

JRM-1 landing impact characteristics from model tests

Date: February 1, 1946
Creator: Pierson, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited performance of N-methylaniline and xylidine blends in an air-cooled aircraft cylinder

Knock-limited performance of N-methylaniline and xylidine blends in an air-cooled aircraft cylinder

Date: February 1, 1946
Creator: Wear, Jerrold D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of control-surface characteristics of plain and balanced flaps on an NACA 0009 elliptical semispan wing

Wind-tunnel investigation of control-surface characteristics of plain and balanced flaps on an NACA 0009 elliptical semispan wing

Date: February 1, 1946
Creator: Silvers, H Norman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analysis of the skipping characteristics of some full-size flying boats

An analysis of the skipping characteristics of some full-size flying boats

Date: January 1946
Creator: Locke, F. W. S., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of gas temperatures from the frequency of knock-induced gas vibrations in an internal-combustion engine

Determination of gas temperatures from the frequency of knock-induced gas vibrations in an internal-combustion engine

Date: January 1, 1946
Creator: Evvard, J C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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