Designing Air Intake Ducts for High Speed Flight

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Designing Air Intake Ducts for High Speed Flight

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dc.contributor.author Kamal, W. A. en_US
dc.date.accessioned 2009-11-25T13:07:12Z
dc.date.available 2009-11-25T13:07:12Z
dc.date.issued 1988 en_US
dc.identifier.citation Engineering Journal of Qatar University, 1988, Vol. 1, Pages 219-239. en_US
dc.identifier.uri http://hdl.handle.net/10576/8019
dc.description.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 intake en_US
dc.language.iso en en_US
dc.publisher Qatar University en_US
dc.subject Fluid systems en_US
dc.title Designing Air Intake Ducts for High Speed Flight en_US
dc.type Article en_US
dc.identifier.pagination 219-239 en_US
dc.identifier.volume 1 en_US

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