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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Month: July
 Collection: Technical Report Archive and Image Library
Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Date: July 1, 1942
Creator: Goranson, R Fabian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calibrations of pitot-static tubes at high speeds

Calibrations of pitot-static tubes at high speeds

Date: July 1, 1942
Creator: Hensley, Reece V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Column strength of magnesium alloy AM-57S

Column strength of magnesium alloy AM-57S

Date: July 1, 1942
Creator: Holt, M
Description: Tests were made to determine the column strength of extruded magnesium alloy AM-57S. Column specimens were tested with round ends and with flat ends. It was found that the compressive properties should be used in computations for column strengths rather than the tensile properties because the compressive yield strength was approximately one-half the tensile yield strength. A formula for the column strength of magnesium alloy AM-57S is given.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the stability and control characteristics of airplanes from tests of powered models

Determination of the stability and control characteristics of airplanes from tests of powered models

Date: July 1, 1942
Creator: Swanson, Robert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Diagrams for calculation of airfoil lattices

Diagrams for calculation of airfoil lattices

Date: July 1, 1942
Creator: Betz, Albert
Description: The field for curved blades is represented by a vortex series with a vortex removed at the blade point. Further, an example of calculation of a curved blade from this series is given, whereby the necessary accuracy required of the different methods in practice is shown according to the case considered.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a new type of low-drag wing-nacelle combination

Experimental investigation of a new type of low-drag wing-nacelle combination

Date: July 1, 1942
Creator: Allen, H. J. & Frick, C. W., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a stall-warning indicator for operation under icing conditions

Flight investigation of a stall-warning indicator for operation under icing conditions

Date: July 1, 1942
Creator: Zalovcik, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Generalized selection charts for bombers powered by one, two, four, and six 2000-horsepower engines

Generalized selection charts for bombers powered by one, two, four, and six 2000-horsepower engines

Date: July 1, 1942
Creator: Hill, Paul R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind-tunnel tests of gun openings in the nose of the fuselage of a 1/4-scale model

High-speed wind-tunnel tests of gun openings in the nose of the fuselage of a 1/4-scale model

Date: July 1, 1942
Creator: Fedziuk, Henry A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of means for extending the range of several bombers to 6000 miles

Investigation of means for extending the range of several bombers to 6000 miles

Date: July 1, 1942
Creator: Harmon, S M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Manganese Investigations - Metallurgical Division: 14. Hydrometallurgical Studies of Manganses Ores

Manganese Investigations - Metallurgical Division: 14. Hydrometallurgical Studies of Manganses Ores

Date: July 1942
Creator: Anderson, Clarence Travis
Description: Report issued by the U.S. Bureau of Mines regarding laboratory tests conducted on acid leaching of manganese ore. Descriptions of the methods used in testing and results are presented. This report contains tables, and graphs.
Contributing Partner: UNT Libraries Government Documents Department
Multiengine airplane spin characteristics as indicated by model tests in the free-spinning wind tunnel

Multiengine airplane spin characteristics as indicated by model tests in the free-spinning wind tunnel

Date: July 1, 1942
Creator: Kamm, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
On a new method for calculating the potential flow past a body of revolution

On a new method for calculating the potential flow past a body of revolution

Date: July 1, 1942
Creator: Kaplan, Carl
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance characteristics of mixed-flow impeller and vaned diffuser with several modifications

Performance characteristics of mixed-flow impeller and vaned diffuser with several modifications

Date: July 1, 1942
Creator: Glodeck, Edward
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Prediction of downwash and dynamic pressure at the tail from free-flight measurements

Prediction of downwash and dynamic pressure at the tail from free-flight measurements

Date: July 1, 1942
Creator: Eujen, E
Description: The present measurements form a continuation of earlier flight tests published in a previous report for predicting the downwash at the tail of an airplane. The method makes use of the tail itself as integrating contact surface to the extent that, beginning from the measurement of the self-alignment of the elevator, the mean downwash angle and dynamic pressure at the tail are determined. The instrumental accuracy is considerably improved if the elevator is completely separate from the controls during the tests, because the effect of friction on the self-alignment of the elevator is then reduced to a minimum and a finer elevator weight balance is rendered possible. The structural design of the push-rod uncoupling mechanism is also described.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary experimental investigation of airfoils in cascade

Preliminary experimental investigation of airfoils in cascade

Date: July 1, 1942
Creator: Daum, Fred L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-Drag Airfoil Sections Suitable for Admitting Air at the Leading Edge

Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-Drag Airfoil Sections Suitable for Admitting Air at the Leading Edge

Date: July 1, 1942
Creator: von Doenhoff, Albert E. & Horton, Elmer A.
Description: An investigation was carried out in the NACA low-turbulence tunnel to develop low-drag airfoil sections suitable for admitting air at the leading edge. A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying the thickness, the camper, the leading-edge radius, and the size of the leading-edge opening. Data are presented giving the characteristics of the airfoil shapes in the range of lift coefficients for high-speed and cruising flight. Shapes have been developed which show no substantial increases in drag over that of the same position along the chord. Many of these shapes appear to have higher critical compressibility speeds than plain airfoils of the same thickness. Low-drag airfoil sections have been developed with openings in the leading edge as large as 41.5 percent of the maximum thickness. The range of lift coefficients for low drag in several cases is nearly as large as that of the corresponding plain airfoil sections. Preliminary measurements of maximum lift characteristics indicate that nose-opening sections of the type herein considered may not produce any marked effects on the maximum lift coefficient.
Contributing Partner: UNT Libraries Government Documents Department
A preliminary investigation of exhaust-gas ejectors for ground cooling

A preliminary investigation of exhaust-gas ejectors for ground cooling

Date: July 1, 1942
Creator: Manganiello, Eugene J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A preliminary investigation of the electrical structure of thunderstorms

A preliminary investigation of the electrical structure of thunderstorms

Date: July 1, 1942
Creator: Workman, E J & Holzer, R E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Wind-Tunnel Tests of the Effect of Nacelles on the Characteristics of a Twin-Engine Bomber Model with Low-Drag Wing, Special Report

Preliminary Wind-Tunnel Tests of the Effect of Nacelles on the Characteristics of a Twin-Engine Bomber Model with Low-Drag Wing, Special Report

Date: July 1, 1942
Creator: Wenzinger, Carl J. & Sivells, James C.
Description: Tests were made in the NACA 19-foot pressure tunnel of a simplified twin-engine bomber model with an NACA low-drag wing primarily to obtain an indication of the effects of engine nacelles on the characteristics of the model both with and without simple split trailing-edge flaps. Nacelles with conventional-type cowlings representative of those used on an existing high-performance airplane and with NACA high-speed type E cowlings were tested. The tests were made without propeller slipstream. The aerodynamic effects of adding the nacelles to the low-drag wing were similar to the effects commonly obtained by adding similar nacelles to conventional wings. The maximum lift coefficient without flaps was slightly increased, but the increment in maximum lift due to deflecting the flaps was somewhat decreased. The stalling characteristics were improved by the presence of the nacelles. Addition of the nacelles had a destabilizing effect on the pitching moments, as is usual for nacelles that project forward of the wing. The drag increments due to the nacelles were of the usual order of magnitude, with the increment due to the nacelles with NACA type E cowlings approximately one-third less than that of the nacelles with conventional cowlings with built-in air scoops.
Contributing Partner: UNT Libraries Government Documents Department
Propeller selection from aerodynamic considerations

Propeller selection from aerodynamic considerations

Date: July 1, 1942
Creator: Talkin, Herbert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of V-G records taken on transport airplanes from 1932 to 1942

Summary of V-G records taken on transport airplanes from 1932 to 1942

Date: July 1, 1942
Creator: Walker, Walter G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of propeller-speed cooling blowers

Tests of propeller-speed cooling blowers

Date: July 1, 1942
Creator: Silverstein, Abe
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile

Two-Dimensional Potential Flow Past an Ordinary Thick Wing Profile

Date: July 1, 1942
Creator: Keune, F.
Description: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
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