Numerical Investigation of Stall Flutter
Abstract
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.
Rights
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