Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : November 16, 2022 - November 18, 2022
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 CD and CM 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.
