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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
Investigation of extreme leading-edge roughness on thick low-drag airfoils to indicate those critical to separation

Investigation of extreme leading-edge roughness on thick low-drag airfoils to indicate those critical to separation

Date: June 1, 1942
Creator: Davidson, Milton
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Normal-pressure tests of rectangular plates

Normal-pressure tests of rectangular plates

Date: June 1, 1942
Creator: Ramberg, Walter; Mcpherson, Albert E & Levy, Samuel
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On the symmetrical potential flow of compressible fluid past a circular cylinder in the tunnel in the subcritical zone

On the symmetrical potential flow of compressible fluid past a circular cylinder in the tunnel in the subcritical zone

Date: June 1, 1942
Creator: Lamla, Ernst
Description: The two-dimensional symmetrical potential flow of compressible fluid past a circular cylinder placed in the center line of a straight tunnel is analyzed in second approximation according to the Jansen-Rayleigh method. The departure of the profile from the exact circular shape can be kept to the same magnitude as for the incompressible flow. The velocities in the narrowest section of the tunnel wall and at the profile edge are discussed in detail.
Contributing Partner: UNT Libraries Government Documents Department
The problem of thermal-expansion stresses in reinforced plastics

The problem of thermal-expansion stresses in reinforced plastics

Date: June 1, 1942
Creator: Turner, P. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Propeller blade stresses caused by periodic displacement of the propeller shaft

Propeller blade stresses caused by periodic displacement of the propeller shaft

Date: June 1, 1942
Creator: Meyer, J
Description: The present report deals with different vibration stresses of the propeller and their removal by an elastic coupling of propeller and engine. A method is described for protecting the propeller from unstable oscillations and herewith from the thus excited alternating gyroscopic moments. The respective vibration equations are set down and the amount of elasticity required is deduced.
Contributing Partner: UNT Libraries Government Documents Department
The stability of laminar flow past a sphere

The stability of laminar flow past a sphere

Date: June 1, 1942
Creator: Pretsch, J
Description: As a contribution to the problem of turbulence on a surface of rotation, the method of small oscillation is applied to the flow past a sphere. It was found that the method developed for two-dimensional flow is applicable without modifications. The frictional layer in the vicinity of the stagnation point of a surface of rotation is less stable against small two-dimensional disturbances than in the stagnation point itself, as proved from an analysis of the velocity distribution made by Homann.
Contributing Partner: UNT Libraries Government Documents Department
Statistical analysis of service stresses in aircraft wings

Statistical analysis of service stresses in aircraft wings

Date: June 1, 1942
Creator: Kaul, Hans W
Description: On the wing structures of modern high speed aircraft, in particular, the comparatively high-service stresses and the consistently increasing number of hours of operation during the life of the separate airplane parts make the studies of strength requirement under recurrent stresses appear of major concern. The DVL has therefore made exhaustive studies for this structural group of airplanes, some results of which are reported here.
Contributing Partner: UNT Libraries Government Documents Department
The strength and stiffness of shear webs with and without lightening holes

The strength and stiffness of shear webs with and without lightening holes

Date: June 1, 1942
Creator: Kuhn, Paul
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Strength tests of thin-walled elliptic duralumin cylinders in pure bending and in combined pure bending and torsion

Strength tests of thin-walled elliptic duralumin cylinders in pure bending and in combined pure bending and torsion

Date: June 1, 1942
Creator: Lundquist, Eugene E & Stowell, Elbridge Z
Description: An analysis is presented of the results of tests made by the Massachusetts Institute of Technology and by the National Advisory Committee for Aeronautics on an investigation of the strength of thin-walled circular and elliptic cylinders in pure bending and in combined torsion and bending. In each of the loading conditions, the bending moments were applied in the plane of the major axis of the ellipse.
Contributing Partner: UNT Libraries Government Documents Department
Strength tests on hulls and floats

Strength tests on hulls and floats

Date: June 1, 1942
Creator: Matthaes, K
Description: The present report deals with strength tests on hulls and floats intended in part for the collection of construction data for the design of these components and in part for the stress analysis of the finished hulls and floats.
Contributing Partner: UNT Libraries Government Documents Department
Stresses around rectangular cut-outs in skin-stringer panels under axial loads I

Stresses around rectangular cut-outs in skin-stringer panels under axial loads I

Date: June 1, 1942
Creator: Moggio, Edwin M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the application of data on various types of flap to the design of fighter brakes

A study of the application of data on various types of flap to the design of fighter brakes

Date: June 1, 1942
Creator: Purser, Paul E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the tightness and flushness of machine-countersunk rivets for aircraft

A study of the tightness and flushness of machine-countersunk rivets for aircraft

Date: June 1, 1942
Creator: Gottlieb, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Study of Turning Performance of a Fighter-Type Airplane Particularly as Affected by Flaps and Increased Supercharging, Special Report

Study of Turning Performance of a Fighter-Type Airplane Particularly as Affected by Flaps and Increased Supercharging, Special Report

Date: June 1, 1942
Creator: Wetmore, J. W.
Description: Results of a study to determine the effects on turning performance due to various assumed modifications to a typical Naval fighter airplane are presented. The modifications considered included flaps of various types, both part and full space, increased supercharging, and increased wing loading. The calculations indicated that near the low-speed end of the speed range, the turning performance, as defined by steady level turns at a given speed, would be improved to some extent by any of the flaps considered at altitudes up to about 25,000 feet. (If turning is not restricted to the conditions of no loss of speed or altitude, more rapid turning can, of course, be accomplished with the aid of flaps, regardless of altitude.) Fowler flaps and NACA slotted flaps appeared somewhat superior to split or perforated split flaps for maneuvering purposes, particularly if the flap position is not adjustable. Similarly, better turning performance should be realized with full-span than with part-span flaps. Turning performance over the lower half of the speed range would probably not be materially improved at any altitude by increased supercharging of the engine unless the propeller were redesigned to absorb the added power more effectively; with a suitable propeller the turning ...
Contributing Partner: UNT Libraries Government Documents Department
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