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Mach number effects on conical surface features of swept shock boundary-layer interactionsA joint experimental and computational study is made of the shock-wave turbulent boundary-layer interaction generated by sharp fins, with emphasis on Mach-number effects. The Mach number range is from 2 to 4 and the unit Reynolds number is from 50 to 80 million per meter. Fin angles are varied from 4 to 22 deg. Surface-flow patterns are obtained using a color surface-flow-visualization technique. The results show that the upstream-influence response in the conical far-field region is a function of the freestream Mach number and the shock strength. A new interpretation of the behavior of the upstream influence with changes of the inviscid shock angle is given. Agreement between the experimental and the computed upstream-influence lines becomes poorer for stronger interactions, with the computations underpredicting the upstream-influence line.
Document ID
19870055141
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lu, F. K.
(Pennsylvania State Univ. University Park, PA, United States)
Settles, G. S.
(Pennsylvania State University University Park, United States)
Horstman, C. C.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 87-1365
Accession Number
87A42415
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-86-0082
CONTRACT_GRANT: NCA2-IR-589-502
Distribution Limits
Public
Copyright
Other

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