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 Decade: 1940-1949
 Year: 1949
 Collection: National Advisory Committee for Aeronautics Collection
Investigations on the stability, oscillation, and stress conditions of airplanes with tab control.  Second partial report : application of the solutions  obtained in the first partial report to tab-controlled airplanes.

Investigations on the stability, oscillation, and stress conditions of airplanes with tab control. Second partial report : application of the solutions obtained in the first partial report to tab-controlled airplanes.

Date: September 1, 1949
Creator: Filzek, B
Description: The first partial report, FB 2000, contained a discussion of the derivation of the equations of motion and their solutions for a tab-controlled airplane; the results obtained there are now to be applied to the longitudinal motion of tab-controlled airplanes. In view of the abundance of structural factors and aerodynamic parameters, a general discussion of the problems is unfeasible. Thus it is demonstrated on the basis of examples what stability, oscillation, and stress conditions are to be expected for tab-controlled airplanes. (author).
Contributing Partner: UNT Libraries Government Documents Department
General Theory of Aerodynamic Instability and the Mechanism of Flutter

General Theory of Aerodynamic Instability and the Mechanism of Flutter

Date: January 1, 1949
Creator: Theodorsen, Theodore
Description: The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Bessel functions of the first and second kind and of zero and first order. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-section theory relating to the steady case. The air forces being known, the mechanism of aerodynamic instability has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been analyzed in detail. An exact solution, involving potential flow and the adoption of the Kutta condition, has been arrived at. The solution is of a simple form and is expressed by means of an auxiliary parameter K.
Contributing Partner: UNT Libraries Government Documents Department
Effect of screens in wide-angle diffusers

Effect of screens in wide-angle diffusers

Date: January 1, 1949
Creator: Schubauer, G B
Description: An experimental investigation at low airspeeds was made of the filling effect observed when a screen or similar resistance is placed across a diffuser. The filling effect is found to be real in that screens can prevent separation or restore separated flow in diffusers even of extreme divergence and to depend principally on screen location and pressure-drop coefficient of the screen. Results are given for three different diffusers of circular cross section with a variety of screen arrangements. Effects of single screens and multiple screens are shown. The mechanics of the filling effect is explained, and possible efficiencies are discussed. Results of arrangements of multiple screens in wide-angle diffusers are given to show a possible application to damping screens as used in wind tunnels to reduce turbulence. (author).
Contributing Partner: UNT Libraries Government Documents Department
The effect of the propeller slipstream on the characteristics of submerged inlets

The effect of the propeller slipstream on the characteristics of submerged inlets

Date: September 9, 1949
Creator: Delany, Noel K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Date: June 1, 1949
Creator: Gothert, B
Description: Report is a brief summary of investigations on symmetrical and cambered airfoils in the DVL high-speed tunnel. Some information on the effects of low aspect ratio are also included.
Contributing Partner: UNT Libraries Government Documents Department
Stability and control data obtained from first flight of X-4 airplane

Stability and control data obtained from first flight of X-4 airplane

Date: February 7, 1949
Creator: Drake, Hubert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Present status of research on boundary-layer control.

Present status of research on boundary-layer control.

Date: January 12, 1949
Creator: Von Doenhoff, Albert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

The effect of air jets simulating chines or multiple steps on the hydrodynamic characteristics of a streamline fuselage

Date: January 7, 1949
Creator: Weinflash, Bernard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

Date: January 20, 1949
Creator: Gadeberg, Burnett L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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