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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Month: June
 Collection: Technical Report Archive and Image Library
Application of Balancing Tabs to Ailerons

Application of Balancing Tabs to Ailerons

Date: June 1, 1942
Creator: Sears, Richard I.
Description: Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effects of rolling velocity and of forces in tab link on aileron hinge moments have been included.
Contributing Partner: UNT Libraries Government Documents Department
Cooling in cruising flight with low fuel-air ratios

Cooling in cruising flight with low fuel-air ratios

Date: June 1, 1942
Creator: Wilson, Herbert A , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Effect of an aromatic mixture added to two 100-octane fuels on engine temperatures and fuel consumption

Date: June 1, 1942
Creator: Jones, Anthony W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of pitch on force and moment characteristics of full-scale propellers of five solidities

The effect of pitch on force and moment characteristics of full-scale propellers of five solidities

Date: June 1, 1942
Creator: Runckel, Jack F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane with Flaps Neutral, Special Report

Effects of Direction of Propeller Rotation on the Longitudinal Stability of the 1/10-Scale Model of the North American XB-28 Airplane with Flaps Neutral, Special Report

Date: June 1, 1942
Creator: Delany, Noel K.
Description: The effects of direction of propeller rotation on factors affecting the longitudinal stability of the XB-28 airplane were measured on a 1/10-scale model in the 7- by 10-foot tunnel of the Ames Aeronautical Laboratory. The main effect observed was that caused by regions of high downwash behind the nacelles (power off as well as power on with flaps neutral). The optimum direction of propeller rotation, both propellers rotating up toward the fuselage, shifted this region off the horizontal tail and thus removed its destabilizing effect. Rotating both propellers downward toward the fuselage moved it inboard on the tail and accentuated the effect, while rotating both propellers right hand had an intermediate result. Comparisons are made of the tail effects as measured by force tests with those predicted from the point-by-point downwash and velocity surveys in the region of the tail. These surveys in turn are compared with the results predicted from available theory.
Contributing Partner: UNT Libraries Government Documents Department
Effects of range of stress and of special notches on fatigue properties of aluminum alloys suitable for airplane propellers

Effects of range of stress and of special notches on fatigue properties of aluminum alloys suitable for airplane propellers

Date: June 1, 1942
Creator: Dolan, Thomas J
Description: Laboratory tests were made to obtain information on the load-resisting properties of X76S-T aluminum alloy when subjected to static, impact, and repeated loads. Results are presented from static-load test of unnotched specimens in tension and in torsion and of notched specimens in tension. Charpy impact values obtained from bend tests on notched specimens and tension impact values for both notched and unnotched specimens tested at several different temperatures are included. The endurance limits obtained from repeated bending fatigue tests made on three different types of testing machine are given for unnotched polished specimens, and the endurance limits of notched specimens subjected to six different ranges of bending stress are also reported. The results indicated that: (a) polished rectangular specimens had an endurance limit about 30 percent less than that obtained for round specimens; (b) a comparison of endurance limits obtained from tests on three different types of machine indicated that there was no apparent effect of speed of testing on the endurance limit for the range of speeds used (1,750 to 13,000 rpm). (c) the fatigue strength (endurance limit) of the X76S-T alloy was greatly decreased by the presence of a notch in the specimens; (d) no complete fractures of ...
Contributing Partner: UNT Libraries Government Documents Department
The fatigue strengths of some wrought aluminum alloys

The fatigue strengths of some wrought aluminum alloys

Date: June 1, 1942
Creator: Stickley, G W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Date: June 1, 1942
Creator: Hoover, Herbert H.
Description: Investigations were undertaken to improve the ailerons of a P-51 fighter so as to obtain greater effectiveness without increasing the stick forces. Modifications consisted of increasing the deflection range of the aileron to 70 percent and changing the original concave section to a thick section with beveled trailing edge. Results of the modified ailerons showed an increase in effectiveness over the original aileron of 70 percent at low speed and 55 percent at high speeds.
Contributing Partner: UNT Libraries Government Documents Department
Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane

Free-spinning-tunnel tests of a 1/23.75-scale model of the Douglas DC-3 airplane

Date: June 1, 1942
Creator: Macdougall, George F , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of loading condition on piloting technique for spin recovery for pursuit airplanes

Influence of loading condition on piloting technique for spin recovery for pursuit airplanes

Date: June 1, 1942
Creator: Seidman, Oscar
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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