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Unsteady pressure measurements on a supercritical airfoil at high Reynolds numbersSteady and unsteady pressures were measured on a 14 percent supercritical airfoil at transonic Mach numbers at Reynolds numbers from 6,000,000 to 35,000,000. Instrumentation techniques were developed to measure unsteady pressures in a cryogenic tunnel at flight Reynolds numbers. Experimental steady data, corrected for wall effects show very good agreement with calculations from a full potential code with an interacted boundary layer. The steady and unsteady pressures both show a shock position that is dependent on Reynolds number. For a supercritical pressure distribution at a chord Reynolds number of 35,000,000 laminar flow was observed between the leading edge and the shock wave at 45 percent chord.
Document ID
19890009888
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hess, R. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1989
Publication Information
Publication: Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2
Subject Category
Aerodynamics
Accession Number
89N19259
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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