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 Decade: 1940-1949
 Year: 1943
 Collection: National Advisory Committee for Aeronautics Collection
Test data on the shear strength of joints assembled with round-head and brazier-head rivets

Test data on the shear strength of joints assembled with round-head and brazier-head rivets

Date: June 1, 1943
Creator: .Schuette, Evan H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section

Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section

Date: November 1, 1943
Creator: Abbott, Frank T , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tail Buffeting

Tail Buffeting

Date: February 1, 1943
Creator: Abdrashitov, G.
Description: An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting.
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the effect of various amounts of aileron droop on the low-speed lateral-control characteristics of an observation airplane

Flight measurements of the effect of various amounts of aileron droop on the low-speed lateral-control characteristics of an observation airplane

Date: August 18, 1943
Creator: Adams, Betty
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the effects of a wing leading-edge slot and other modifications on the stability, maximum lift, and high speed of an observation airplane

Flight measurements of the effects of a wing leading-edge slot and other modifications on the stability, maximum lift, and high speed of an observation airplane

Date: January 19, 1943
Creator: Adams, Betty
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A subpress for compressive tests

A subpress for compressive tests

Date: December 1, 1943
Creator: Aitchison, C S & Miller, James A
Description: A subpress for compressive tests is described. The subpress was designed primarily for use in developing and investigating methods for testing thin sheet metal in compression. Provision was made for testing fixed-end and flat-end specimens with or without various types of lateral support against buckling. Compressive stress-strain data for a sheet of 0.032-inch 24S-RT aluminum alloy were obtained with the subpress by the pack method and by the single-thickness method. The data showed small scatter and the stress-strain curves obtained by the two methods were in close agreement.
Contributing Partner: UNT Libraries Government Documents Department
Tensile and compressive tests of magnesium alloy J-1 sheet

Tensile and compressive tests of magnesium alloy J-1 sheet

Date: December 1, 1943
Creator: Aitchison, C S & Miller, James A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Date: October 1, 1943
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A method for calculating heat transfer in the laminar flow region of bodies

A method for calculating heat transfer in the laminar flow region of bodies

Date: January 1, 1943
Creator: Allen, H Julian & Look, Bonne C
Description: This report has been prepared to provide a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited in use to the determination of heat transfer from the forward section of such bodies when the flow is laminar. A comparison of the calculated average heat-transfer coefficient for the nose section of the wing of a Lockheed 12-A airplane with that experimentally determined shows a satisfactory agreement. A sample calculation is appended.
Contributing Partner: UNT Libraries Government Documents Department
The problem of longitudinal stability and control at high speeds

The problem of longitudinal stability and control at high speeds

Date: November 1, 1943
Creator: Allen, H. Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

The Effect of Compressibility on the Growth of the Laminar Boundary Layer on Low-Drag Wings and Bodies

Date: January 1, 1943
Creator: Allen, H. Julian & Nitzberg, Gerald E.
Description: The development of the laminar boundary layer in a compressible fluid is considered. Formulas are given for determining the boundary-layer thickness and the ratio of the boundary-layer Reynolds number to the body Reynolds number for airfoils and bodies of revolution. It i s shown that the effect of compressibility will profoundly alter the Reynolds number corresponding to the upper limit of the range of the low-drag coefficients . The available data indicate that for low-drag and high critical compressibility speed airfoils and bodies of revolution, this effect is favorable.
Contributing Partner: UNT Libraries Government Documents Department
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Date: September 1, 1943
Creator: Allen, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil

Date: August 1, 1943
Creator: Anderson, R A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Pressure distribution measurements on various surfaces of a 0.2375-scale model of the Douglas XA-26 airplane in the 19-foot pressure tunnel

Pressure distribution measurements on various surfaces of a 0.2375-scale model of the Douglas XA-26 airplane in the 19-foot pressure tunnel

Date: October 1, 1943
Creator: Ashworth, C Dixon
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of varying percentages of exhaust gas on engine performance

Effect of varying percentages of exhaust gas on engine performance

Date: April 1, 1943
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lead susceptibility of paraffins, cycloparaffins, and olefins

Lead susceptibility of paraffins, cycloparaffins, and olefins

Date: May 1, 1943
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion

Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion

Date: May 1, 1943
Creator: Bartone, Leonard M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Fatigue characteristics of spot-welded 24S-T aluminum alloy

Fatigue characteristics of spot-welded 24S-T aluminum alloy

Date: June 1, 1943
Creator: Beaver, W. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Hydrodynamic-stability tests of a model of a flying boat and of a planing surface having a small downward projection (hook) on the planing bottom near the step

Hydrodynamic-stability tests of a model of a flying boat and of a planing surface having a small downward projection (hook) on the planing bottom near the step

Date: January 1, 1943
Creator: Benson, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Full-scale tunnel tests of a flying model of the Curtiss XP-55 airplane

Full-scale tunnel tests of a flying model of the Curtiss XP-55 airplane

Date: January 1, 1943
Creator: Biebel, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Wind-tunnel tests of ailerons at various speeds II : ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil

Date: June 1, 1943
Creator: Bird, J D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters XII : performance of a formed-plate crossflow exhaust gas and air heat exchanger

An investigation of aircraft heaters XII : performance of a formed-plate crossflow exhaust gas and air heat exchanger

Date: August 1, 1943
Creator: Boelter, L M K; Guibert, A G; Dennison, H G & Morrin, E H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters XIII : performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers

An investigation of aircraft heaters XIII : performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers

Date: August 1, 1943
Creator: Boelter, L M K; Guibert, A G; Miller, M A & Morrin, E H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters VIII : a simplified method for the calculation of the unit thermal conductance over wings

An investigation of aircraft heaters VIII : a simplified method for the calculation of the unit thermal conductance over wings

Date: March 1943
Creator: Boelter, L. M. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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