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 Decade: 1940-1949
 Year: 1943
 Month: May
 Collection: National Advisory Committee for Aeronautics Collection
Characteristics of an NACA 66, S-209 section hydrofoil at several depths

Characteristics of an NACA 66, S-209 section hydrofoil at several depths

Date: May 1, 1943
Creator: Land, Norman S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of powered propellers on the aerodynamic characteristics and the porpoising stability of a dynamic model of a long-range flying boat

Effect of powered propellers on the aerodynamic characteristics and the porpoising stability of a dynamic model of a long-range flying boat

Date: May 1, 1943
Creator: Land, Norman S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Emergency measures for increasing the range of fighter airplanes

Emergency measures for increasing the range of fighter airplanes

Date: May 1, 1943
Creator: Wetmore, Joseph W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Formulas for propellers in yaw and charts of the side-force derivative

Formulas for propellers in yaw and charts of the side-force derivative

Date: May 1, 1943
Creator: Ribner, Herbert S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-spinning-tunnel tests of a model of a canard airplane

Free-spinning-tunnel tests of a model of a canard airplane

Date: May 1, 1943
Creator: Pepoon, Philip W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane

Full-scale tunnel investigation of the pressure distribution over the tail of the P-47B airplane

Date: May 1, 1943
Creator: Dingeldein, Richard C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Heat Transfer to a Plate in Flow at High Speed

The Heat Transfer to a Plate in Flow at High Speed

Date: May 1, 1943
Creator: Eckert, E. & Drewitz, O.
Description: The heat transfer in the laminar boundary layer of a heated plate in flow at high speed can be obtained by integration of the conventional differential equations of the boundary layer, so long as the material values can be regarded as constant. This premise is fairly well satisfied at speeds up to about twice the sonic speed and at not excessive temperature rise of the heated plate. The general solution of the equation includes Pohlhausen's specific cases of heat transfer to a plate at low speeds and of the plate thermometer. The solution shows that the heat transfer coefficient at high speed must be computed with the same equation as at low speed, when it is referred to the difference of the wall temperature of the heated plate in respect to its "natural temperature." Since this fact follows from the linear structure of the differential equation describing the temperature field, it is equally applicable to the heat transfer in the turbulent boundary layer.
Contributing Partner: UNT Libraries Government Documents Department
An instrument for the determination of rain densities in flight

An instrument for the determination of rain densities in flight

Date: May 1, 1943
Creator: Houghton, Henry G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Jet-boundary corrections for reflection-plane models in rectangular wind tunnels

Jet-boundary corrections for reflection-plane models in rectangular wind tunnels

Date: May 1, 1943
Creator: Toll, Thomas A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Large-deflection theory of curved sheet

Large-deflection theory of curved sheet

Date: May 1, 1943
Creator: Levy, Samuel
Description: Equations are given for the elastic behavior of initially curved sheets in which the deflections are not small in comparison with the thickness, but at the same time small enough to justify the use of simplified formulas for curvature. These equations are solved for the case of a sheet with circular cylindrical shape simply supported along two edges parallel to the axis of the generating cylinder. Numerical results are given for three values of the curvature and for three ratios of buckle length to buckle width. The computations are carried to buckle deflections of about twice the sheet thickness. It was concluded that initial curvature may cause an appreciable increase in the buckling load but that, for edge strains which are several times the buckling strain, the initial curvature causes a negligibly small change in the effective width.
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
The longitudinal shear strength required in double-angle columns of 24S-T aluminum alloy

The longitudinal shear strength required in double-angle columns of 24S-T aluminum alloy

Date: May 1, 1943
Creator: Moggio, Edwin M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Method of calculating performance of dual-rotating propellers from airfoil characteristics

Method of calculating performance of dual-rotating propellers from airfoil characteristics

Date: May 1, 1943
Creator: Naiman, Irven
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Notes on maximum airplane angular velocities

Notes on maximum airplane angular velocities

Date: May 1, 1943
Creator: Conway, H M
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
Some effects of Reynolds and Mach numbers on the lift of an NACA 0012 rectangular wing in the NACA 19-foot pressure tunnel

Some effects of Reynolds and Mach numbers on the lift of an NACA 0012 rectangular wing in the NACA 19-foot pressure tunnel

Date: May 1, 1943
Creator: Muse, Thomas C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of exhaust propulsion nozzles

Tests of exhaust propulsion nozzles

Date: May 1, 1943
Creator: Campbell, Paul J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of a retractable planing flap instead of a fixed step on a seaplane

The use of a retractable planing flap instead of a fixed step on a seaplane

Date: May 1, 1943
Creator: Lina, Lindsay J
Description: None
Contributing Partner: UNT Libraries Government Documents Department