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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Collection: Technical Report Archive and Image Library
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane

Date: May 1, 1942
Creator: Abbott, Frank T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Preliminary Low-Drag-Airfoil and Flap Data from Tests at Large Reynolds Numbers and Low Turbulence

Date: March 1, 1942
Creator: Abbott, I. H.; Davidson, M. & Jacobs, E. N.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Interference effects of longitudinal flat plates on low-drag airfoils

Interference effects of longitudinal flat plates on low-drag airfoils

Date: November 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Date: January 1, 1942
Creator: Abbott, Ira H
Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Contributing Partner: UNT Libraries Government Documents Department
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Date: January 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons

Date: June 1, 1942
Creator: Abbott, Ira H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report

Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report

Date: December 1, 1942
Creator: Abbott, Ira H. & Miller, Ralph B.
Description: Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Aerodynamic Heat-Power Engine Operating on a Closed Cycle

Date: November 1, 1942
Creator: Ackeret, J. & Keller, D. C.
Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
Contributing Partner: UNT Libraries Government Documents Department
Metal- and Nonmetal-Mine Accidents in the United States During the Calendar Year 1940 (Excluding Coal Mines)

Metal- and Nonmetal-Mine Accidents in the United States During the Calendar Year 1940 (Excluding Coal Mines)

Date: 1942
Creator: Adams, W. W. & Kolhos, M. E.
Description: Report published by the U.S. Bureau of Mines regarding accidents at mines located in the United States for all operations except coal mines. The report includes statistics about the number and kinds of accidents as well as information about the mining operations (i.e., number of persons employed, average amount of work performed per person, etc.).
Contributing Partner: UNT Libraries Government Documents Department
Quarry Accidents in the United States During the Calendar Year 1940

Quarry Accidents in the United States During the Calendar Year 1940

Date: 1942
Creator: Adams, William & Wrenn, Virginia E.
Description: Report published by the U.S. Bureau of Mines which is a compilation of accidents in quarries located in the United States with data regarding the number and kinds of accidents as well as information about the mining operations (e.g., number of men employed, kinds of quarries, amount of work performed, etc.).
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Accidents in the United States, 1939

Coal-Mine Accidents in the United States, 1939

Date: 1942
Creator: Adams, William W.; Geyer, L. E. & Parry, M. G.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatal and non-fatal accidents in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Accidents in the United States, 1940

Coal-Mine Accidents in the United States, 1940

Date: 1942
Creator: Adams, William W.; Geyer, L. E. & Parry, M. G.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatal and non-fatal accidents in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
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
Wind-tunnel investigation of control-surface characteristics V : the use of a beveled trailing edge to reduce the hinge moment of a control surface

Wind-tunnel investigation of control-surface characteristics V : the use of a beveled trailing edge to reduce the hinge moment of a control surface

Date: March 1, 1942
Creator: Ames, Milton B , Jr
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
Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank

Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank

Date: October 1, 1942
Creator: Ashworth, C Dixon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tensile and pack compressive tests of some sheets of aluminum alloy, 1025 carbon steel, and chromium-nickel steel

Tensile and pack compressive tests of some sheets of aluminum alloy, 1025 carbon steel, and chromium-nickel steel

Date: February 1, 1942
Creator: Atchison, C S & Miller, James A
Description: Tensile and compressive stress-strain curves, stress-deviation curves, and secant modulus-stress curves are given for longitudinal and transverse specimens of 17S-T, 24S-T, and 24S-RT aluminum-alloy sheet in thicknesses from 0.032 to 0.081 inch, 1025 carbon steel sheet in thicknesses of 0.054 and 0.120 inch, and chromium-nickel steel sheet in thicknesses form 0.020 to 0.0275 inch. Significant differences were found between the tensile and the compressive stress-strain curves, and also the corresponding corollary curves; similarly, differences were found between the curves for the longitudinal and transverse directions. These differences are of particular importance in considering the compressive strength of aircraft structures made of thin sheet. They are explored further for the case of compression by giving tangent modulus-stress curves in longitudinal and transverse compression and dimensionless curves of the ratio of tangent modulus to Young's modulus and of the ratio of reduced modulus for a rectangular section to Young's modulus, both plotted against the ratio of stress to secant yield strength.
Contributing Partner: UNT Libraries Government Documents Department
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
Effect of changes in aspect ratio, side area, flight-path angle, and normal acceleration on lateral stability

Effect of changes in aspect ratio, side area, flight-path angle, and normal acceleration on lateral stability

Date: December 1, 1942
Creator: Bamber, M J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-speed tests of radial-engine nacelles on a thick low-drag wing

High-speed tests of radial-engine nacelles on a thick low-drag wing

Date: May 1, 1942
Creator: Becker, John V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane

High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane

Date: January 1, 1942
Creator: Becker, John V & LEONARD LLOYD H
Description: Report presents the results of force tests made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed tunnel to investigate compressibility and interference effects of speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model, tests were made with several modifications designed to reduce the drag and to increase the critical speed.
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
Test of single-stage axial-flow fan

Test of single-stage axial-flow fan

Date: January 1, 1942
Creator: Bell, E Barton
Description: A single-stage axial fan was built and tested in the shop of the propeller-research tunnel of the NACA. The fan comprised a simple 24-blade rotor having a diameter of 21 inches and a solidity of 0.86 and a set of 37 contravanes having a solidity of 1.33. The rotor was driven by a 25-horsepower motor capable of rotating at a speed of 3600 r.p.m. The fan was tested for volume, pressure, and efficiency over a range of delivery pressures and volumes for a wide range of contravane and blade-angle settings. The test results are presented in chart form in terms of nondimensional units in order that similar fans may be accurately designed with a minimum effort. The maximum efficiency (88 percent) was obtained by the fan at a blade angle of 30 degrees and a contravane angle of 70 degrees. An efficiency of 80 percent was obtained by the fan with the contravanes removed.
Contributing Partner: UNT Libraries Government Documents Department
The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull

The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull

Date: May 1, 1942
Creator: Benson, James M.
Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
Contributing Partner: UNT Libraries Government Documents Department
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