The effects of quadratic constitutive relation of turbulence models on the drag prediction of wing-body configuration

Numerical investigations of the NASA Common Research Model from the 6th AIAA CFD Drag Prediction Workshop are performed with in-house solver MFlow. The results of linear viscosity model and nonlinear viscosity model with quadratic constitutive relation taken in to account are compared with experimental data. It is found that at angles-of-attack above 3.5 degrees, linear viscosity model over-estimates the separation at the corner of wing-body junction, therefore the results deviates from the experimental data. However, the turbulence model with Quadratic constitutive relation can improve the prediction of the secondary flow at the corner and leads to better agreement with experimental data. The causes of the difference between two models on the prediction are revealed through the analysis of local flow and pressure distribution at the corner.