Numerical Investigation of Stall Flutter

[+] Author and Article Information
J. A. Ekaterinaris

Navy–NASA Joint Institute of Aeronautics, NASA Ames Research Center, Moffett Field, CA 94035

M. F. Platzer

Department of Aeronautics and Astronautics, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 118(2), 197-203 (Apr 01, 1996) (7 pages) doi:10.1115/1.2836626 History: Received February 25, 1994; Online January 29, 2008


Unsteady, separated, high Reynolds number flow over an airfoil undergoing oscillatory motion is investigated numerically. The compressible form of the Reynolds-averaged governing equations is solved using a high-order, upwind biased numerical scheme. The turbulent flow region is computed using a one-equation turbulence model. The computed results show that the key to the accurate prediction of the unsteady loads at stall flutter conditions is the modeling of the transitional flow region at the leading edge. A simplified criterion for the transition onset is used. The transitional flow region is computed with a modified form of the turbulence model. The computed solution, where the transitional flow region is included, shows that the small laminar/transitional separation bubble forming during the pitch-up motion has a decisive effect on the near-wall flow and the development of the unsteady loads. Detailed comparisons of computed fully turbulent and transitional flow solutions with experimental data are presented.

Copyright © 1996 by The American Society of Mechanical Engineers
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