CASPERによる軍用機形態のNavier-Stokesシミュレーション(流体工学,流体機械)  [in Japanese] Navier-Stokes Simulation of Military Aircraft Configuration Using CASPER  [in Japanese]

In high-Reynolds number flow problems, very fine and stretched grids are generally required to resolve accurately thin boundary layers developed along the body surface and so the application of the tetrahedral unstructured grids has several difficulties in computational efficiency and solution accuracy. One promising approach is to use a hybrid unstructured grid technique for the boundary layers; prism, pyramid, tent and tetrahedron. In this paper, the hybrid unstructured grid technique is incorporated into a CFD-based design system, CASPER. To validate the present CFD codes, we carried out the Reynolds-Averaged Navier-Stokes simulations of a military aircraft configuration such as an F-16A in both subsonic and supersonic regions. On wing surface pressure coefficient distributions, longitudinal, lateral and directional forces and moments, the present computed results are quantitatively compared to the wind-tunnel testing data, the Euler computed and the multi-block structured N-S computed results.