Designing Air Intake Ducts for High Speed Flight

Show simple item record

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


Files in this item

This item appears in the following Collection(s)

Show simple item record