Numerical inverstigation and discussion on CHN-T1 benchmark model using Spalart-Allmaras model and SSG/LRR-ω model

By solving Reynolds averaged Navier-Stokes equations, all cases of the CHN-T1 benchmark aircraft configuration from the first AeCW-1 conference were investigated in detail using Spalart-Allmaras model and Reynolds stress model, respectively. The behaviors of the two models on this test case were specifically discussed and investigated, in order to evaluate the ability regarding approach the grid convergence, the accuracy for the prediction of the aircraft operating near the buffeting envelop, as well as the sensitivity of the two models to Reynolds number. After comparing the computations with the experimental data, the main conclusions are organized as the following:Both turbulence models can achieve final grid convergence, and the RSM can faster grid convergence than the S-A model. For the cases with high angles of attack, where shock-induced separation can occur, the computations using the two models significantly differ to each other. The tail-supporting string of the CHN-T1 model has a great impact on the pressure distribution of the horizontal tail. The present of the tail-supporting string induces a complex turbulence separation on the tail of the fuselage, which is difficult to be predicted accurately. The computations with the static aeroelastic deformation yield poor agreement of the moment coefficient with the experimental data, especially for the RSM model. For cases operating at higher Reynolds number, the results predicted by the two models are closer.