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Proposed aeroelastic and flutter tests for the National Transonic FacilityTests that can exploit the capability of the NTF and the transonic cryogenic tunnel, or lead to improvements that could enhance testing in the NTF are discussed. Shock induced oscillation, supersonic single degree control surface flutter, and transonic flutter speed as a function of the Reynolds number are considered. Honeycombs versus screens to smooth the tunnel flow and a rapid tunnel dynamic pressure reducer are recommended to improve tunnel performance.
Document ID
19810022602
Document Type
Conference Paper
Authors
Stevenson, J. R. (Rockwell International Corp. Los Angeles, CA, United States)
Date Acquired
August 11, 2013
Publication Date
September 1, 1981
Publication Information
Publication: NASA. Langley Research Center High Reynolds Number Res. - 1980
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810022588Analytic PrimaryHigh Reynolds number research - 1980