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Experimental Investigation of Crossing Shock Wave-Turbulent Boundary Layer-Bleed InteractionResults of an experimental investigation of a symmetric crossing shock wave/turbulent boundary layer/bleed interaction are presented for a freestream unit Reynolds number of 1.68 x 10(exp 7)/m, a Mach number of 2.81, and deflection angles of 8 degrees. The data obtained in this study are bleed mass flow rate using a trace gas technique, qualitative information in the form of oil flow visualization, flow field Pitot pressures, and static pressure measurements using pressure sensitive paint. The main objective of this test is two-fold. First, this study is conducted to explore boundary layer control through mass flow removal near a large region of separated flow caused by the interaction of a double fin-induced shock wave and an incoming turbulent boundary layer. Also, a comprehensive data set is needed for computational fluid dynamics code validation.
Document ID
19970009931
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kim, Hyun
(NASA Lewis Research Center Cleveland, OH United States)
Hingst, Warren R.
(NASA Lewis Research Center Cleveland, OH United States)
Davis, David O.
(NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-107392
AIAA Paper 97-0608
NAS 1.15:107392
E-10592
Meeting Information
Meeting: Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 6, 1997
End Date: January 10, 1997
Sponsors: American Inst. of Aeronautics and Astronautics
Accession Number
97N15576
Funding Number(s)
PROJECT: RTOP 505-62-52
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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