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UNT Libraries Government Documents Department
Decade:
1940-1949
Serial/Series Title:
NACA Advanced Restricted Report
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
Permallink:digital.library.unt.edu/ark:/67531/metadc61385/
An analysis of the skipping characteristics of some full-size flying boats
Date: January 1, 1946
Creator: Locke, F W S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc60904/
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
Permallink:digital.library.unt.edu/ark:/67531/metadc62384/
The effect of lateral area on the lateral stability and control characteristics of an airplane as determined by tests of a model in the Langley free-flight tunnel
Date: January 1, 1946
Creator: Drake, Hubert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61005/
Experimental determination of the effect of negative dihedral on lateral stability and control characteristics at high lift coefficients
Date: January 1, 1946
Creator: Mckinney, Marion O , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61002/
Single-cylinder engine tests of porous chrome-plated cylinder barrels with special bore coatings for radial air-cooled engines
Date: January 1, 1946
Creator: Anderson, Roy I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61909/
Spray characteristics of a powered dynamic model of a flying boat having a hull with a length-beam ratio of 9.0
Date: January 1, 1946
Creator: Bell, Joe W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61787/
Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination I : Performance of a Highly Supercharged Compression-Ignition Engine
Date: December 1, 1945
Creator: Sanders, J. C.
Description: Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62108/
The effect of concentrated loads on flexible rings in circular shells
Date: December 1, 1945
Creator: Griffith, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc61657/
Effect of propeller-axis angle of attack on thrust distribution over the propeller disk in relation to wake-survey measurement of thrust
Date: December 1, 1945
Creator: Pendley, Robert E
Description: Tests were made to investigate the variation of thrust distribution over the propeller disk with angle of pitch of the propeller thrust axis and to determine the disposition and the minimum number of rakes necessary to measure the propeller thrust. The tests were made at a low Mach number for a low and a high blade angle with the propeller operating at three small angles of pitch, and some of the tests were repeated at a higher Mach number. The data obtained show that, for small angles of pitch, large changes occur in the energy distribution in the wake which prohibit the use of a single survey rake for thrust measurement in flight tests and limit the use of a single rake in wind-tunnel tests. Under certain conditions, the energy distribution in the wake took on a symmetrical form and two diametrically opposed survey rakes were shown to be satisfactory for obtaining propeller thrust. (author).
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc65446/