Transport Wing Flutter Model Transonic Limit Cycle Oscillation Test

Autor:	Charles V. Spain, John W. Edwards, Donald F. Keller, Robert W. Moses, David M. Schuster
Rok vydání:	2009
Předmět:	Wing root Engineering business.industry Angle of attack Aerospace Engineering Mechanics Aeroelasticity Flow separation Classical mechanics Limit cycle Flutter Wingtip device business Transonic
Zdroj:	Journal of Aircraft. 46:1104-1113
ISSN:	1533-3868 0021-8669
DOI:	10.2514/1.30079
Popis:	The model for aeroelastic validation research involving computation semispan wind-tunnel model, a transport wing-fuselage flutter model, was tested in NASA Langley's Transonic Dynamics Tunnel with the goal of obtaining experimental limit cycle oscillation behavior data at transonic separation onset conditions. This research model is notable for its inexpensive construction and instrumentation installation procedures. Unsteady pressures and wing responses were obtained for three wing-tip configurations: clean, tip store, and winglet. Traditional flutter boundaries were measured over the range of M = 0.6-0.9, and maps of limit cycle oscillation behavior were made in the range of M = 0.85-0.95. The effects of dynamic pressure and angle of attack were measured. Testing in both R134a heavy gas and air provided unique data on the Reynolds number, transition effects, and the effect of speed of sound on limit cycle oscillation behavior. This report gives an overview of the test results, including experimental flutter boundaries, and the conditions involving shock-induced transonic flow separation onset at low wing angles, including maps of limit cycle oscillation behavior.
Databáze:	OpenAIRE
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