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Boundary-layer transition on a plate subjected to simultaneous spanwise and chordwise pressure gradientsThe boundary-layer transition on a short plate was studied by means of the china-clay visual technique. The plate model was mounted in a wind tunnel so that it was subjected to small simultaneous spanwise and chordwise pressure gradients. Results of the experimental study, which was performed at three subsonic velocities, indicated that the transition pattern was appreciably curved in the spanwise direction but quite smooth and well behaved. Reasonable comparisons between predictions of transition and experiment were obtained from two finite-difference two-dimensional boundary-layer calculation methods which incorporated transition models based on the concept of a transition intermittency factor.
Document ID
19740025322
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Boldman, D. R. (NASA Lewis Research Center Cleveland, OH, United States)
Brinich, P. F. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
September 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
E-7979
NASA-TM-X-3107
Accession Number
74N33435
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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