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Unsteady transition measurements on a pitching three-dimensional wingBoundary layer transition measurements were made during an experimental study of the aerodynamics of a rectangular wing undergoing unsteady pitching motions. The wing was tested at chordwise Mach numbers between 0.2 and 0.6, at sweep angles of 0, 15, and 30 deg, and for steady state, sinusoidal, and constant pitch rate motions. The model was scaled to represent a full size helicopter rotor blade, with chord Reynolds numbers between 2 and 6 x 10(exp 6). Sixteen surface hot-film gages were located along three spanwise stations: 0.08, 0.27, and 0.70 chords from the wing tip. Qualitative heat transfer information was obtained to identify the unsteady motion of the point of transition to turbulence. In combination with simultaneous measurements of the unsteady surface pressure distributions, the results illustrate the effects of compressibility, sweep, pitch rate, and proximity to the wing tip on the transition and relaminarization locations.
Document ID
19930018261
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lorber, Peter F. (United Technologies Research Center East Hartford, CT, United States)
Carta, Franklin O. (United Technologies Research Center East Hartford, CT, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Publication Information
Publication: California State Univ., The Fifth Symposium on Numerical and Physical Aspects of Aerodynamic Flows
Subject Category
Aircraft Stability And Control
Accession Number
93N27450
Funding Number(s)
CONTRACT_GRANT: DAAL03-89-C-0013
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19930018238Collected WorksThe Fifth Symposium on Numerical and Physical Aspects of Aerodynamic Flows
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