Parallel computation of flow fields around a space-plane has been conducted on the Numerical Wind Tunnel (NWT) at the National Aerospace Laboratory, aiming to apply the compressible Navier-Stokes code which super/transonic flows with to solve low subsonic flow have been simulated fields. Computational results show its sufficient reliability in terms of predicting aerodynamic forces. Thus, a prospect to make the present code a robust flow solver covering from a low subsonic to a supersonic regime with modifications has been obtained. To realize it, further more effort is needed to get convergence efficiency of computation and to analyze the mechanism of microscopic flow phenomena.
スペースプレーンまわりの低マッハ数流れの数値計算
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