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Dynamic stall phenomena have been investigated numerically by solving incompressible Navier-Stokes equations with a third- order upwind scheme in order to reveal the flow structure and mechanism of dynamic stall. The separated flows around a wing section at static attack angle are calculated and compared with the experiments which are conducted by the present authors. The results show excellent agreements with the experiments and the numerical scheme is proved to work well. Separated flows around oscillating airfoil in pitch are calculated by using the scheme and a moving mesh system. The flow conditions are selected from our experiments. The calculated separated region is small in pitching-up process and it becomes large in a pitching-down process. Quite different characteristics of flow patterns between in a pitching-up and pitching-down processes are obtained.

For the fundamental study of aerodynamic heating of winged vehicle and space planes in hypersonic flow the detailed structure of three-dimensional shock wave/turbulent boundary layer interaction region induced by sweptback sharp fins are investigated carefully by oil flow technique and pressure distribution. The major objectives of the present study are to study the effects of the shape of the leading edge of the fin to the flow fields on the body and to study the effect of the sweep angle of the leading edge of the fin to the interaction region. Also aerodynamic heating phenomena in the flow fields are investigated by using a new technique. For the measurements a new method of measuring heat flux developed by the present authors are used. The new method is based on a new type of thin-film heat transfer gauge with high spatial resolution and fast response.