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Shuttle orbiter boundary layer transition at flight and wind tunnel conditionsHypersonic boundary layer transition data obtained on the windward centerline of the Shuttle orbiter during entry for the first five flights are presented and analyzed. Because the orbiter surface is composed of a large number of thermal protection tiles, the transition data include the effects of distributed roughness arising from tile misalignment and gaps. These data are used as a benchmark for assessing and improving the accuracy of boundary layer transition predictions based on correlations of wind tunnel data taken on both aerodynamically rough and smooth orbiter surfaces. By comparing these two data bases, the relative importance of tunnel free stream noise and surface roughness on orbiter boundary layer transition correlation parameters can be assessed. This assessment indicates that accurate predications of transition times can be made for the orbiter at hypersonic flight conditions by using roughness dominated wind tunnel data. Specifically, times of transition onset and completion is accurately predicted using a correlation based on critical and effective values of a roughness Reynolds number previously derived from wind tunnel data.
Document ID
19840002082
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Goodrich, W. D.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Derry, S. M.
(NASA Lyndon B. Johnson Space Center Houston, TX, United States)
Bertin, J. J.
(Texas Univ. Austin, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1983
Publication Information
Publication: NASA. Langley Research Center Shuttle Performance: Lessons Learned, Pt. 2
Subject Category
Space Transportation
Accession Number
84N10149
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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