22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-4.7.5

SHOCK STALL FLUTTER A TWO-DIMENSIONAL AIRFOIL

M. Yamasaki, T. Uchida, I. Yukimura, K. Isogai
Department of Aeronautics and Astronautics, Kyushu University, Japan

Keywords: flutter, shock stall, two-dimensional airfoil, flow visualization

In the experiment using the single-degreeof- freedom (pitching)-flutter model which simulates the typical section of a forward swept wing, the large scale shock-induced flow separation characterizing ‘Shock-Stall Flutter’ has been observed by a schlieren system with a high speed video camera. The experimental results are compared with the computational ones to evaluate the numerical analysis code.

view full paper