Vectored thrust control.
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Authors
Horais, Brian John
Subjects
vectored thrust control
Advisors
Hokenson, Gustave J.
Date of Issue
1972-12
Date
December 1972
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
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.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
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.