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A Theory for Subsonic and Transonic Flow over a Cone - with or without Small Yaw Angle
TENNESSEE UNIV SPACE INST TULLAHOMA
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The primary purpose was to develop an accurate method of calculating the surface pressure distribution over a conical forebody for a wide range of free-stream Mach numbers including subsonic, transonic, and low supersonic flow. The theoretical approach used was similar to one previously proposed by Wu and Aoyama. The nondimensionalized small disturbance transonic flow equation was linearized to a variable coefficient elliptic form. A transformation was introduced to further reduce the governing equation to a Laplace form, which yields an integral equation for the transformation function. A first-order solution was obtained by an iterative procedure. The effect due to the small angle of attack has been included by adding the linearized cross flow contribution.
APPROVED FOR PUBLIC RELEASE