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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1942
 Month: October
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel

Date: October 1942
Creator: Liddell, Robert B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane

Date: October 1942
Creator: Underwood, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Annual Report of the Mining Division, Fiscal Year 1942

Annual Report of the Mining Division, Fiscal Year 1942

Date: October 1942
Creator: Jackson, Charles F.
Description: Report issued by the U.S. Bureau of Mines on the annual work conducted by the Mining Division during 1942. Descriptions of projects and operations during the fiscal year are listed. This report contains tables, and photographs.
Contributing Partner: UNT Libraries Government Documents Department
Beam and torsion tests of aluminum-alloy 615-T tubing

Beam and torsion tests of aluminum-alloy 615-T tubing

Date: October 1, 1942
Creator: Moore, R L & Holt, Marshall
Description: Tests were made to determine the effect of length and the effect of ratios of diameter to wall thickness upon the flexural and torsional moduli of failure of 61S-T aluminum-alloy tubing. The moduli of failure in bending, as determined by tests in which the tubing was loaded on the neutral axis at the one-third points of the span, were found to bear an approximately linear relationship with diameter-thickness ratio and were practically independent of span within the limits investigated. Empirical equations are given describing the relations obtained. The moduli of failure in torsion were found to be dependent upon length as well as upon diameter-thickness ratios. Empirical equations are given for predicting strengths within the range of plastic buckling. Within the elastic range, available torsion theories were found to be satisfactory.
Contributing Partner: UNT Libraries Government Documents Department
The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

Date: October 1, 1942
Creator: Hantzsche, W. & Wendt, H.
Description: For the tunnel corrections of compressible flows those profiles are of interest for which at least the second approximation of the Janzen-Rayleigh method can be applied in closed form. One such case is presented by certain elliptical symmetrical cylinders located in the center of a tunnel with fixed walls and whose maximum velocity, incompressible, is twice the velocity of flow. In the numerical solution the maximum velocity at the profile and the tunnel wall as well as the entry of sonic velocity is computed. The velocity distribution past the contour and in the minimum cross section at various Mach numbers is illustrated on a worked out-example.
Contributing Partner: UNT Libraries Government Documents Department
Contribution to the Design of Plywood Shells

Contribution to the Design of Plywood Shells

Date: October 1, 1942
Creator: Blumrich, S.
Description: The writer sets out to prove by calculation and experiment that by extensive utilization of the skin to carry axial load (reduction of stringer spacing) the stringer sections can be made small enough to afford a substantial saving in structural weight. This saving ranges from 5 to about 40 percent.
Contributing Partner: UNT Libraries Government Documents Department
Effect of countersunk depth on the tightness of two types of machine-countersunk rivet

Effect of countersunk depth on the tightness of two types of machine-countersunk rivet

Date: October 1, 1942
Creator: Gottlieb, Robert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of dead rise upon the low-angle type of porpoising

The effect of dead rise upon the low-angle type of porpoising

Date: October 1, 1942
Creator: Lina, Lindsay J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Elevator stick forces in spins as computed from wind-tunnel measurements

Elevator stick forces in spins as computed from wind-tunnel measurements

Date: October 1, 1942
Creator: Klinar, J W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A flight investigation of the stability of a towed body

A flight investigation of the stability of a towed body

Date: October 1, 1942
Creator: Phillips, W H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the rudder control and sideslip characteristics of four vertical tail arrangements on the P-40 series airplanes

Flight measurements of the rudder control and sideslip characteristics of four vertical tail arrangements on the P-40 series airplanes

Date: October 1, 1942
Creator: Vensel, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer in the Turbulent Boundary Layer of a Compressible Gas at High Speeds

Heat Transfer in the Turbulent Boundary Layer of a Compressible Gas at High Speeds

Date: October 1, 1942
Creator: Frankl, F.
Description: The Reynolds law of heat transfer from a wall to a turbulent stream is extended to the case of flow of a compressible gas at high speeds. The analysis is based on the modern theory of the turbulent boundary layer with laminar sublayer. The investigation is carried out for the case of a plate situated in a parallel stream. The results are obtained independently of the velocity distribution in the turbulent boundar layer.
Contributing Partner: UNT Libraries Government Documents Department
The influence of impact velocity on the tensile characteristics of some aircraft metals and alloys

The influence of impact velocity on the tensile characteristics of some aircraft metals and alloys

Date: October 1, 1942
Creator: Clark, Donald S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters I : elementary heat transfer considerations in an airplane

An investigation of aircraft heaters I : elementary heat transfer considerations in an airplane

Date: October 1942
Creator: Boelter, L. M. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters II : properties of gases

An investigation of aircraft heaters II : properties of gases

Date: October 1942
Creator: Boelter, L. M. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters III : measured and predicted performance of double tube heat exchangers

An investigation of aircraft heaters III : measured and predicted performance of double tube heat exchangers

Date: October 1942
Creator: Boelter, L. M. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters IV : measured and predicted performance of longitudinally finned tubes

An investigation of aircraft heaters IV : measured and predicted performance of longitudinally finned tubes

Date: October 1942
Creator: Boelter, L. M. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel

Date: October 7, 1942
Creator: Erickson, Albert L
Description: A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6-scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal maneuverability improved by the substitution of a long symmetrical fuselage for the standard fuselage.
Contributing Partner: UNT Libraries Government Documents Department
On the distribution of stress in a thin plate elastically supported along two edges at loads beyond the stability limit

On the distribution of stress in a thin plate elastically supported along two edges at loads beyond the stability limit

Date: October 1, 1942
Creator: Dunn, Louis G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of two-stage turbosupercharger using mixed-flow impellers

Performance of two-stage turbosupercharger using mixed-flow impellers

Date: October 1, 1942
Creator: King, J Austin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Shear-lag tests of two box beams with flat covers loaded to destruction

Shear-lag tests of two box beams with flat covers loaded to destruction

Date: October 1, 1942
Creator: Chiarito, Patrick T
Description: None
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
Tests of a large spherical turret and a modified turret on a typical bomber fuselage

Tests of a large spherical turret and a modified turret on a typical bomber fuselage

Date: October 1, 1942
Creator: Mattson, Axel T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical distribution of load over a swept-back wing

Theoretical distribution of load over a swept-back wing

Date: October 1, 1942
Creator: Cohen, Doris
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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