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Author Kamal, W. A.en_US
Author Anwar, Anwar E. M.en_US
Available date 2009-11-25T13:07:12Zen_US
Publication Date 1988en_US
Publication Name Engineering Journal of Qatar University
Citation Engineering Journal of Qatar University, 1988, Vol. 1, Pages 219-239.en_US
URI http://hdl.handle.net/10576/8019en_US
Abstract A proven duct flow model is used to examine the influence of the intake duct geometric and inlet flow parameters on the pressure recovery performance of intake ducts for high speed flight. The geometric parameters include: the inlet parallel pipe length, the diffuser cone angle, the length of the faired transition from the pipe to diffuser cone as well as the degree of the fairing. The inlet flow parameters examined are: the boundary layer momentum thickness, the velocity profile shape and the turbulence level. The inlet parameter values used simulate those following a normal shock wave — turbulent boundary layer interaction inside the intake duct, i.e. they simulate the conditions at the inlet to the diffuser of a supersonic intakeen_US
Language enen_US
Publisher Qatar Universityen_US
Subject Fluid systemsen_US
Title Designing Air Intake Ducts for High Speed Flighten_US
Type Articleen_US
Pagination 219-239en_US
Volume Number 1en_US


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