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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Advanced Restricted Report
High-altitude cooling. III : Radiators

High-altitude cooling. III : Radiators

Date: September 1, 1944
Creator: Nielsen, Jack Norman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of methods for computing drag from wake surveys at high subsonic speeds

Theoretical investigation of methods for computing drag from wake surveys at high subsonic speeds

Date: June 1, 1945
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An empirical formula for the critical shear stress of curved sheets

An empirical formula for the critical shear stress of curved sheets

Date: January 1, 1945
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Measurement of Fuel-Air Ratio by Analysis of the Oxidized Exhaust Gas

The Measurement of Fuel-Air Ratio by Analysis of the Oxidized Exhaust Gas

Date: October 1, 1943
Creator: Memm, J. Lawrence, Jr.
Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy Fuel Specification, No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs or the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Piston-Head Temperature on Knock-Limited Power

The Effect of Piston-Head Temperature on Knock-Limited Power

Date: July 1, 1944
Creator: Imming, Harry S.
Description: To determine the effect of piston-head temperature on knock-limited power. Tests were made in a supercharged CFR engine over a range of fuel-air ratios from 0.055 to 0.120, using S-3 reference fuel, AN-F-28, Amendment-2, aviation gasoline, and AN-F-28 plus 2 percent xylidines by weight. Tests were run at a compression ratio of 7.0 with inlet-air temperatures of 150 F and 250 F and at a compression ratio of 8.0 with an inlet-air temperature of 250 F. All other engine conditions were held constant. The piston-head temperature was varied by circulation of oil through passages in the crown of a liquid-cooled piston. This method of piston cooling decreased the piston-head temperature about 80 F. The data are not intended to constitute a recommendation as to the advisability of piston cooling in practice.
Contributing Partner: UNT Libraries Government Documents Department
Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 24S-T Aluminum Alloy

Column and Plate Compressive Strengths of Aircraft Structural Materials: Extruded 24S-T Aluminum Alloy

Date: July 1, 1945
Creator: Heimerl, George J.
Description: Column and plate compressive strengths of extruded 24S-T aluminum alloy were determined both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-,and channel-section columns. These tests are part of an extensive research investigation to provide data on the' structural strength of various aircraft materials. The results are presented in the form of curves and charts that are suitable for use in the design and analysis of aircraft structures.
Contributing Partner: UNT Libraries Government Documents Department
Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam rotating with constant angular velocity about a transverse axis through the root

Date: June 1, 1945
Creator: Stowell, Elbridge Z
Description: A theoretical investigation was made of the behavior of a cantilever beam in rotational motion about a transverse axis through the root determining the stresses, the deflections, and the accelerations that occur in the beam as a result of the arrest of motion. The equations for bending and shear stress reveal that, at a given percentage of the distance from root to tip and at a given trip velocity, the bending stresses for a particular mode are independent of the length of the beam and the shear stresses vary inversely with the length. When examined with respect to a given angular velocity instead of a given tip velocity, the equations reveal that the bending stress is proportional to the length of the beam whereas the shear stress is independent of the length. Sufficient experimental verification of the theory has previously been given in connection with another problem of the same type.
Contributing Partner: UNT Libraries Government Documents Department
The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

Date: June 1, 1943
Creator: Klein, Milton M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Porpoising: a comparison of theory with experiment

Porpoising: a comparison of theory with experiment

Date: July 1, 1943
Creator: Suarez, Anthony
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of developed width on strength of axially loaded curved sheet stringer panels

Effect of developed width on strength of axially loaded curved sheet stringer panels

Date: November 1, 1944
Creator: Zibritosky, George
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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