For the verification and validation of SSG/LRR-ωReynolds stress model, four typical two dimensional cases from NASA turbulence resources website were chosen, including zero pressure gradient flat plate, bump-in-channel, airfoil near-wake and flow over NACA0012 airfoil. A part of numerical results were in good agreement with that of CFL3D. For flow over NACA0012 airfoil, lift coefficients of Reynolds stress model and SA model were compared. It is obvious that near the stall angle of attack, Reynolds stress model has advantages over SA model. Based on these results, SSG/LRR-ωReynolds stress model was applied to the simulation of complex DLR-F6 wingbody configuration. Pressure coefficient in typical stations is comparable to that of experiment. Besides, small range of separation in the wing-body intersection is well captured. 