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Experimental study of three shock wave/turbulent boundary layer interactionsThe paper presents a systematic study of the supersonic flow of a turbulent boundary layer over several compression-corner models. The wind tunnel and the compression-corner models (ramps fitted with aerodynamic fences to minimize three-dimensional effects) were identical with those used by Settles et al. (1979); constant-temperature hot-wire anemometry was used for the mass-flow measurements. The turning angles used for the compression corners were 8, 16, and 20 deg. In all three flow cases, the shock wave/turbulent flow interaction did amplify the turbulent stresses dramatically, with amplification increasing with increasing turning angle. However, different stress components were amplified by different amounts.
Document ID
19880027234
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Smits, Alexander J.
(Princeton Univ. NJ, United States)
Muck, Kin-Choong
(Princeton University NJ, United States)
Date Acquired
August 13, 2013
Publication Date
September 1, 1987
Publication Information
Publication: Journal of Fluid Mechanics
Volume: 182
ISSN: 0022-1120
Subject Category
Aerodynamics
Accession Number
88A14461
Funding Number(s)
CONTRACT_GRANT: AF-AFOSR-85-0126
CONTRACT_GRANT: NAGW-240
Distribution Limits
Public
Copyright
Other

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