階層型直交格子と埋め込み境界法を用いた航空機高揚力形態の空力予測

抄録

In this study, the steady RANS simulation around CRM-HL is conducted to investigate the prediction capability of the hierarchical Cartesian grid flow solver to predict the aerodynamic performance of an aircraft high lift configuration. To calculate the turbulent boundary layer, the immersed boundary method and the wall function are used. Three types of grids are used, and their grid numbers are about 100M, 200M, and 400M. The calculated aerodynamic coefficients agreed well with the wind tunnel test results in the low angle of attack region. On the other hand, the calculated aerodynamic coefficients showed a discrepancy in the aerodynamics coefficients to the wind tunnel test at high angle of attack. In addition, grid convergence could not be confirmed for C_D and C_M at high angle of attack. However, the RANS method used in this paper is not a model which can capture physical phenomena related to separation. Hence, reasonable results for RANS were obtained semi-automatically through automatic grid generation.