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Three-dimensional hypersonic transitional/turbulent mean flow profiles.Detailed three-dimensional compressible transitional/turbulent boundary-layer profiles are presented for use as test cases in numerical and integral calculation procedures. The profiles were obtained from tests conducted in the Mach 20 leg of the Langley High Reynolds Number Helium Facility. The presented data represent an arduous test case for analytical prediction methods, since 'low Reynolds number' and precursor transition effects should probably be accounted for to accurately predict the boundary-layer growth and development.
Document ID
19730051392
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fischer, M. C.
Weinstein, L. M. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 7, 2013
Publication Date
July 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 73-635
Report Number: AIAA PAPER 73-635
Meeting Information
Meeting: Fluid and Plasma Dynamics Conference
Location: Palm Springs, CA
Start Date: July 16, 1973
End Date: July 18, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
73A36194
Distribution Limits
Public
Copyright
Other

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