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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Month: May
 Collection: Technical Report Archive and Image Library
Bending of Rectangular Plates with Large Deflections

Bending of Rectangular Plates with Large Deflections

Date: May 1, 1942
Creator: Levy, Samuel
Description: The solution of von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, McPherson, and Levy. The deflections for a square plate under lateral pressure are compared with experimental and theoretical results by Kaiser. It is found that the effective widths agree closely with Marguerre's formula and with the experimentally observed values and that the deflections agree with the experimental results and with Kaiser's work.
Contributing Partner: UNT Libraries Government Documents Department
A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

A Brief Study of the Speed Reduction of Overtaking Airplanes by Means of Air Brakes, Special Report

Date: May 1, 1942
Creator: Pearson, H. A. & Amderspm. R. F.
Description: As an aid to airplane designers interested in providing pursuit airplanes with decelerating devices intended to increase the firing time when overtaking another airplane, formulas are given relating the pertinent distances and speeds in horizontal flight to the drag increase required. Charts are given for a representative parasite-drag coefficient from which the drag increase, the time gained, and the closing distance may be found. The charts are made up for three values of the ratio of the final speed of the pursuing airplane to the speed of the pursued airplane and for several values of the ratio of the speed of the pursued airplane to the initial speed of the pursuing airplane. Charts are also given indicating the drag increases obtainable with double split flaps and with conventional propellers. The use of the charts is illustrated by an example in which it is indicated that either double split flaps or, under certain ideal conditions, reversible propellers should provide the speed reductions required.
Contributing Partner: UNT Libraries Government Documents Department
The development of satisfactory flying qualities on the Douglas dive bomber, model SBD-1 through flight testing successive modifications in control-surface area, hinge-line location, and aerodynamic-balance nose shape

The development of satisfactory flying qualities on the Douglas dive bomber, model SBD-1 through flight testing successive modifications in control-surface area, hinge-line location, and aerodynamic-balance nose shape

Date: May 1, 1942
Creator: Root, L E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of additions of aromatics on the knocking characteristics of several 100-octane fuels at two engine speeds

Effect of additions of aromatics on the knocking characteristics of several 100-octane fuels at two engine speeds

Date: May 1, 1942
Creator: Harries, Myron L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of inlet-air velocity distribution on the metering pressure of an injection-type aircraft carburetor

Effect of inlet-air velocity distribution on the metering pressure of an injection-type aircraft carburetor

Date: May 1, 1942
Creator: Kinghorn, George F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

A flight investigation of internally balanced sealed ailerons in the presence of a balanced split flap

Date: May 1, 1942
Creator: Williams, W C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A flight investigation of short-period longitudinal oscillations of an airplane with free elevator

A flight investigation of short-period longitudinal oscillations of an airplane with free elevator

Date: May 1, 1942
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Generalized selection charts for bombers with four 2000-horsepower engines

Generalized selection charts for bombers with four 2000-horsepower engines

Date: May 1, 1942
Creator: Hill, Paul R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Ground effect on downwash angles and wake location

Ground effect on downwash angles and wake location

Date: May 1, 1942
Creator: Katzoff, S & Sweberg, Harold H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-Speed Tests of a Ducted Body with Various Air-Outlet Openings

High-Speed Tests of a Ducted Body with Various Air-Outlet Openings

Date: May 1, 1942
Creator: Becker, John V. & Baals, Donald D.
Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture and a high critical speed. An air inlet at the nose and various outlets at the tail were added: drag and internal-flow data were obtained over the given speed range. The critical speed of the ducted bodies was found to be as high as that of the streamline body. The external - drag with air flow through the body did not exceed the drag of the basic streamline shape. No appreciable variation in the efficiency of the diffuser section of the internal duct occurred throughout the Mach number range of the tests.
Contributing Partner: UNT Libraries Government Documents Department
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