Tokyo University of Agriculture and Technology Faculty of Technology
Tokyo University of Agriculture and Technology Faculty of Technology
National Aerospace Laboratory
National Aerospace Laboratory
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
The full Navier-Stokes equations were solved numerically by using a parallel computer at National Aerospace Laboratory (NAL) to simulate oblique reflection of plane shock waves over a rigid wall. The dependent hyperbolic conservation forms for finite volume cells were integrated by applying a second order Total Variation Diminishing (TVD) scheme. The three stage Runge-Kutta method was used for time integration. Various types of Riemann solvers of both the Euler and the Navier-Stokes were tested to compare the accuracy of the results. The present numerical simulations show that the results computed by the Euler code showed good reflection patterns of the shock waves but the complicated flow fields behind the Mach stem were not well computed. The lambda shock wave created in front of the corner of a wedge was not simulated by the Euler code. The present scheme based on the Harten-Yee type TVD scheme coupled with Roe's approximate solver gave fairly good results in predicting various types of shock reflection. In the present computation the use of two-four parallel processors was effective.
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nalsp0027028.pdf
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