Equations are developed using the source distribution method for the velocity potential function and pressure on thin wings in steady and unsteady motion. Closed form solutions are given for harmonically oscillating wings of general plan form including the effect of the wing wake. Some useful examples are presented in an appendix for arrow, semielliptical, and hexagonal plan form wings
A computer program has been developed to account approximately for the effects of finite wing thickn...
A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic ...
Linearized theory for compressible unsteady flow is used to derive the velocity potential and lift a...
This thesis presents a more accurate and efficient method for the study of finite span wings in ste...
A series of publications on the source-distribution methods for evaluating the aerodynamics of thin ...
The problem of oscillating lifting surface of finite span in subsonic compressible flow is reduced t...
Equations are developed using the source distribution method for the velocity potential function and...
A finite difference method for the solution of the transonic flow about a harmonically oscillating w...
As part of an investigation of flows around and forces on an oscillating finite wing in subsonic com...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
Analytical and empirical studies of a finite difference method for the solution of the transonic flo...
This paper constitutes a theoretical study of the aerodynamic forces on an oscillating or steady win...
Details are given of a numerical solution of the integral equation which relates oscillatory or stea...
The problem of the oscillating lifting surface of finite span in subsonic compressible flow is reduc...
A theoretical study, based on the linearized equations of motion for small disturbance, is made of t...
A computer program has been developed to account approximately for the effects of finite wing thickn...
A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic ...
Linearized theory for compressible unsteady flow is used to derive the velocity potential and lift a...
This thesis presents a more accurate and efficient method for the study of finite span wings in ste...
A series of publications on the source-distribution methods for evaluating the aerodynamics of thin ...
The problem of oscillating lifting surface of finite span in subsonic compressible flow is reduced t...
Equations are developed using the source distribution method for the velocity potential function and...
A finite difference method for the solution of the transonic flow about a harmonically oscillating w...
As part of an investigation of flows around and forces on an oscillating finite wing in subsonic com...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
Analytical and empirical studies of a finite difference method for the solution of the transonic flo...
This paper constitutes a theoretical study of the aerodynamic forces on an oscillating or steady win...
Details are given of a numerical solution of the integral equation which relates oscillatory or stea...
The problem of the oscillating lifting surface of finite span in subsonic compressible flow is reduc...
A theoretical study, based on the linearized equations of motion for small disturbance, is made of t...
A computer program has been developed to account approximately for the effects of finite wing thickn...
A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic ...
Linearized theory for compressible unsteady flow is used to derive the velocity potential and lift a...
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