Abstract
In an experiment using a single-degree-of-freedom (pitching) flutter model, which simulates the typical section of a forward-swept wing, shock-stall flutter, which is induced by large-scale shock-induced flow separation, has been observed by a schlieren system with a high-speed video camera. The experimental results are compared with computational ones to evaluate the numerical analysis code using the compressible Navier-Stokes equations. The mechanism of the shock-stall flutter is made clear by considering the relations between the pitching moments vs angle of attack and the flow patterns around the airfoil, which are obtained by the experimental flow visualization and the numerical simulation
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