2次元BCMを用いた主翼―尾翼間の空力干渉の研究

抄録

In this study, a two-dimensional compressible block-structured Cartesian mesh CFD solver was used to perform a numerical analysis of the cross-sectional shapes of the NASA-CRM main and tail wings. The purpose is to investigate the influence of aerodynamic interference between the main wing and the tail. As a result, it was revealed that the lift coefficient and the pitching moment coefficient tend to increase by employing finer mesh. In addition, the flowfields slightly differ with/without the refinement between the main wing and the tail when the wake from the main wing affects the tail.