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Supercritical flow about a thick circular-arc airfoilThe supercritical flow about a biconvex circular-arc airfoil is being thoroughly documented at Ames Research Center in order to provide experimental test cases suitable for guiding and evaluating current and future computer codes. The effects of angle of attack, effects of leading and trailing-edge splitter plates, additional unsteady pressure fluctuation (buffeting) measurements and glow-field shadowgraphs, and application of an oil-film technique to display separated-wake streamlines were studied. Computed and measured pressure distributions for steady and unsteady flows, using a recent computer code representative of current methodology, are compared. It was found that the numerical solutions are often fundamentally incorrect in that only strong (shock-polar terminology) shocks are captured, whereas experimentally, both strong and weak shock waves appear.
Document ID
19790008629
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mcdevitt, J. B. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
A-7693
NASA-TM-78549
Accession Number
79N16800
Funding Number(s)
PROJECT: RTOP 505-06-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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