非構造格子ソルバーTASコードとMEGG3D非構造格子による遷音速NASA Common Research Model解析

抄録

In response to the First and Second Aerodynamics Prediction Challenges, held in Tokyo, July 2015 and in Kanazawa, July 2016, respectively, computational fluid dynamics simulations were performed for the NASA Common Research Model using the Tohoku University Aerodynamic Simulation (TAS) Code. Our results were summarized in this manuscript, with an emphasis on key computational techniques and mesh generation methods. Unstructured hybrid meshes were generated using the Mixed-Element Grid Generator in 3 Dimensions (MEGG3D), and were deformed based on wing deformation data obtained during wind tunnel testing. The effects of support system interference, of mesh density and of laminar to turbulent boundary layer transition are shown to discuss the validity of computational results. Aerodynamic coefficients were well predicted at low angles of attack when the support system interference effect was considered, while an accurate prediction of pitching moment at high angles of attack was challenging because mesh density affected the shock location on the wing and the size of side-of-body separation.