computational procedure using three-dimensional Euler equations has beendeveloped to predict flows over integrated inlet systems of supersonic flighters ormissiles. The solution of 3-D Euler equations is based on fini...computational procedure using three-dimensional Euler equations has beendeveloped to predict flows over integrated inlet systems of supersonic flighters ormissiles. The solution of 3-D Euler equations is based on finite volume spatialdiscretization and multi-step Runge-Kuttta time marching schemes proposed byJameson in 1981. In order to suppress its well-known tendency for odd-even pointdecoupling and to minimize pre- and post-shock oscillations, an adaptive dissipation term is added to the system. A non-overlapping domain decomposition technique is used to achieve the required geometric fiexibility and to relieve computermemory capacity requirement. Detailed method is given for the flux interpolationacross the interfaces between adjacent subdomains, and full solution procedure isalso presented. Numerical simulations at three flight states have been implementedfor a supersonic missile which has a complex outer shape. Satisfactory results areobtained.展开更多
文摘computational procedure using three-dimensional Euler equations has beendeveloped to predict flows over integrated inlet systems of supersonic flighters ormissiles. The solution of 3-D Euler equations is based on finite volume spatialdiscretization and multi-step Runge-Kuttta time marching schemes proposed byJameson in 1981. In order to suppress its well-known tendency for odd-even pointdecoupling and to minimize pre- and post-shock oscillations, an adaptive dissipation term is added to the system. A non-overlapping domain decomposition technique is used to achieve the required geometric fiexibility and to relieve computermemory capacity requirement. Detailed method is given for the flux interpolationacross the interfaces between adjacent subdomains, and full solution procedure isalso presented. Numerical simulations at three flight states have been implementedfor a supersonic missile which has a complex outer shape. Satisfactory results areobtained.
