A high-order numerical simulation of the Common Research Model (CRM) wing-body test model is presented by solving Reynolds-Averaged Navier-Stokes (RANS) equations with the fifth-order Weighted Compact Nonlinear Scheme (WCNS) and multi-block 1-to-1 structured grid. The test model and initial conditions are obtained from the sixth AIAA Drag Prediction Workshop (DPW Ⅵ). The purpose of present work is to assess the influence of the static aeroelastic deformation and support system on the numerical results of the CRM wing-body configuration by using high-order numerical method. Compared to the numerical results of the "rigid" CRM wing-body configuration and the experimental data from the NASA National Transonic Facility (NTF) wind tunnel, the high-order numerical results show that for 3.0° angle of attack, the static aeroelastic deformation moves the shock wave upward on the wing upper surface, and decreases the negative pressure before the shock wave; the support system moves the shock wave further upward and changes the flow structure near the wing tip. The main reason for the lift curve break at 4.0° angle of attack is that the computational model does not include the support system. The numerical results with the addition of the static aeroelastic deformation and support system into the calculation model match the experimental results more closely.
WANG Yuntao
,
MENG Dehong
,
SUN Yan
,
LI Wei
. High-order numerical simulation of CRM-WB wind tunnel model[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018
, 39(4)
: 121642
-121642
.
DOI: 10.7527/S1000-6893.2017.21642
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