| There are complicated interactions between shock wave and boundary layer nearby hinge when the flap angel changes in supersonic flight. Because of the separation induced by shock wave, the efficiency of flap reduces. In this thesis, the phenomenon of shock-wave/boundary-layer interaction in the practical flight is researched. Thus, the following works have been conducted.1, The thorough study of several discrimination schemes (central or upwind) on the building principle and dissipation models is conducted with a comparison of the individual characters. The typical high order interpolation methods, MUSCL extrapolation, are investigated on the basic mechanism of damping the possible nonphysical oscillations near the local extreme. A detailed investigation on the abilities of two kinds of slop limiters is also presented.2, The matured one-equation S-A and B-L turbulence model are compared with different flows. After simulating two- dimensional transonic flow with two turbulence models, FDS-Roe scheme is verified. As a result, such a numerical approach can be presented: MUSCL extrapolation with nonlinear limiter can ensure to obtain second order accuracy. With the thin-layer assumption, N-S equations can be resolved numerically with FDS-Roe scheme. The S-A turbulence model is used, too.3, The research work on interaction of shock wave with boundary layer is reviewed and summarized in this thesis. The numerical simulation of diamond aerofoil in supersonic flow by the means of CFD has been conducted. Comparing with the computation by program and the exact analytical results, it can be easily found that the efficiency of flap reduce because of the interaction between shock wave and boundary layer. |
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