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Vectored thrust control.

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Author
Horais, Brian John
Date
1972-12
Advisor
Hokenson, Gustave J.
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Abstract
Supersonic two-dimensional flow from a nozzle with the exit plane inclined to the central axis of the nozzle will be turned if the exit pressure of the nozzle is not matched to the external pressure. The direction and magnitude of the flow deflection angle and the resulting deflection force is a function of the exit pressure of the nozzle, the exit Mach number and the amount the exit plane is inclined to the central axis of the nozzle. A study of the deflection forces and deflection angles generated for a Mach number range of 1.2 to 2.4 and for a wide range of exit pressures is presented in this paper.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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http://hdl.handle.net/10945/16426
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  • 1. Thesis and Dissertation Collection, all items

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