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Experimental and numerical investigation of an oblique shock wave/turbulent boundary layer interaction with continuous suctionAn numerical and experimental investigation has been conducted into the interaction of an incident oblique shock wave with a turbulent boundary layer, for the cases of a rough plate and a porous plate with suction, at a nominal Mach number of 2.5 and flow deflection angles of 0, 4, 6, and 8 deg. Attention is given to the pitot pressure profiles, wall static pressures, and porous plate local bleed distributions measured for the two plates. Suction is found to increase the strength of the incident shock required to separate the boundary layer; for all shock strengths tested, separation is completely eliminated.
Document ID
19890041036
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Benhachmi, Driss
(Case Western Reserve Univ. Cleveland, OH, United States)
Greber, Isaac
(Case Western Reserve University Cleveland, OH, United States)
Hingst, Warren R.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-0357
Accession Number
89A28407
Funding Number(s)
CONTRACT_GRANT: NAG3-61
Distribution Limits
Public
Copyright
Other

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