Hypersonic crossing shock-wave/turbulent-boundary-layer interactionsExperimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flow field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows.
Document ID
19930040866
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kussoy, M. I. (NASA Ames Research Center Moffett Field, CA, United States)
Horstman, K. C. (Eloret Inst. Palo Alto, CA, United States)
Horstman, C. C. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0781
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit