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Crossing shock wave turbulent boundary layer interactions - Variable angle and shock generator length geometry effects at Mach 3By comparing the detailed wall static pressure distributions for 9 inch and 11 inch long fins generating a crossing shock configuration at M = 2.93, the high resolution results of the 9 inch fins are shown to be free of exit effects. Analysis of the static pressure profiles have delineated the limited regions where the single fin results are valid. The characteristics of the complex interaction, with varying shock wave strength, have been described. The data provide a critical test for computational fluid dynamics which, in its initial phase, has performed poorly in predicting the measured wall static pressure distributions.
Document ID
19920044390
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bogdonoff, S. M.
(NASA Ames Research Center Moffett Field, CA, United States)
Stokes, W. L.
(Princeton University NJ, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-0636
Accession Number
92A27014
Funding Number(s)
CONTRACT_GRANT: NAG2-718
Distribution Limits
Public
Copyright
Other

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