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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Month: September
 Collection: Technical Report Archive and Image Library
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: September 1, 1942
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of tightness of 78 degrees machine-countersunk rivets driven in holes prepared with 78 degrees and 82 degrees countersinking tools

Comparison of tightness of 78 degrees machine-countersunk rivets driven in holes prepared with 78 degrees and 82 degrees countersinking tools

Date: September 1, 1942
Creator: Mandel, Merven W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Condensation trails : where they occur and what can be done about them

Condensation trails : where they occur and what can be done about them

Date: September 1, 1942
Creator: Pearson, H A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The critical compression load for a universal testing machine when the specimen is loaded through knife edges

The critical compression load for a universal testing machine when the specimen is loaded through knife edges

Date: September 1, 1942
Creator: Lundquist, Eugene E
Description: The results of a theoretical and experimental investigation to determine the critical compression load for a universal testing machine are presented for specimens loaded through knife edges. The critical load for the testing machine is the load at which one of the loading heads becomes laterally instable in relation to the other. For very short specimens the critical load was found to be less than the rated capacity given by the manufacturer for the machine. A load-length diagram is proposed for defining the safe limits of the test region for the machine. Although this report is particularly concerned with a universal testing machine of a certain type, the basic theory which led to the derivation of the general equation for the critical load, P (sub cr) = alpha L can be applied to any testing machine operated in compression where the specimen is loaded through knife edges. In this equation, L is the length of the specimen between knife edges and alpha is the force necessary to displace the upper end of the specimen unit horizontal distance relative to the lower end of the specimen in a direction normal to the knife edges through which the specimen is loaded.
Contributing Partner: UNT Libraries Government Documents Department
A description of the Ju 88 airplane anti-icing equipment

A description of the Ju 88 airplane anti-icing equipment

Date: September 1, 1942
Creator: Jackson, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The direct-stress fatigue strength of 17S-T aluminum alloy throughout the range from 1/2 to 500,000,000 cycles of stress

The direct-stress fatigue strength of 17S-T aluminum alloy throughout the range from 1/2 to 500,000,000 cycles of stress

Date: September 1, 1942
Creator: Hartmann, E C
Description: Fatigue-test were conducted on six specimens made from 3/4-inch-diameter 17S-T rolled-and-drawn rod for the purpose of obtaining additional data on the fatigue life of the material at stresses up to the static strength. The specimens were tested in direct tension using a stress range from zero to a maximum in tension. A static testing machine was used to apply repeated loads in the case of the first three specimens; the other three specimens were tested in a direct tension-compression fatigue machine. The direct-stress fatigue curve obtained for the material indicates that, in the range of stresses above about two-thirds the tensile strength, the fatigue strength is higher than might be expected by simply extrapolating the ordinary curve of stress plotted against the number of cycles determined at lower stresses.
Contributing Partner: UNT Libraries Government Documents Department
Effect of aromatics and spark advance on thermal efficiency

Effect of aromatics and spark advance on thermal efficiency

Date: September 1, 1942
Creator: Gilbert, Mitchell
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of cowling shape on the stability characteristics of an airplane

The effect of cowling shape on the stability characteristics of an airplane

Date: September 1, 1942
Creator: Letko, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of ground on characteristics of model of a low-wing airplane with full-span slotted flap with and without power

Effect of ground on characteristics of model of a low-wing airplane with full-span slotted flap with and without power

Date: September 1, 1942
Creator: Wallace, A R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of valve cooling upon maximum permissible engine output as limited by knock

The effect of valve cooling upon maximum permissible engine output as limited by knock

Date: September 1, 1942
Creator: Munger, Maurice
Description: A Wright GR-1820-G200 cylinder was tested over a wide range of fuel-air ratios at maximum permissible power output as limited by knock with three different degrees of valve cooling. The valves used were stock valves (solid inlet valve and hollow sodium-cooled exhaust valve), hollow valves with no coolant, and hollow valves with flowing water as a coolant. Curves showing the variation in maximum permissible values of inlet-air pressure, indicated mean effective pressure, cylinder charge, and indicated specific fuel consumption with change in fuel-air ratio and valve cooling are shown. The use of valves cooled by a stream of water passing through their hollow interiors permitted indicated mean effective pressures 10 percent higher than the mean effective pressures permissible with stock valves when the engine was operated with fuel-air ratios from 0.055 to 0.065. Operation of the engine with lean mixtures with uncooled hollow valves resulted in power output below the output obtained with the stock valves. The data show an increase in maximum permissible indicated mean effective pressure due to cooling the valves, which averages only 2.1 percent with fuel-air ratios from 0.075 to 0.105.
Contributing Partner: UNT Libraries Government Documents Department
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