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Shock boundary layer interaction control in supersonic intake using cavity with porous surface
, M. Kaushik, K.P. Sinhamahapatra
Published in American Institute of Aeronautics and Astronautics Inc, AIAA
In jet engines, it is imperative to bring down the flow speeds from supersonic to subsonic level before entering the burner, in order to have efficient combustion. It is achieved by a series of oblique as well as normal shock waves in supersonic intakes. However, the advantage of shock enabled compression in intakes does not come standalone but with colossal losses due to shock-boundary layer interactions, which includes intake unstart, abrupt thickening/separation of boundary layer, etc. Here, an attempt is made to control the interactions at the shock impact point in a Mach 2.2 mixed compression intake. Passive control in the form of a shallow cavity covered with porous surface, is employed at the shock impingement point. The porosity of the surface is varied as 10%, 15.7% and 22.5% and their effect in controlling the SBLIs at different intake contraction ratios of 1.14, 1.19 and 1.25 is studied. The intake controlled by cavity with 15.7% porous surface reduces the interaction losses. These results are found to be in good agreement with the qualitative data. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
About the journal
JournalData powered by Typeset35th AIAA Applied Aerodynamics Conference, 2017
PublisherData powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Impact Factor1.868
Citation Styleunsrt
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