Effects of the boundary layer transition on the global aerodynamic coefficients

The numerical results for global aerodynamic coefficients and overall flow topology obtained with the Langtry-Menter γ − Reθ transitional model are compared with previous results obtained with Sparlat-Allmaras, Menter SST and cubic k − ε turbulence models. The numerical simulations are performed using configuration “one” from the 1st AIAA CFD High-Lift Prediction Workshop as the testbed, which is a trapezoidal wing with a 30 deg. slat deflection and a full-span flap with 25 deg. deflection. The numerical simulations are accomplished with the CFD++ solver considering the Reynolds-averaged Navier-Stokes formulation (RANS). The hexahedral mesh approach is here considered and the results are obtained for a hexahedral mesh with 22.8 million cells. Experimental data from NASA Langley 14 by 22-foot Subsonic Wind Tunnel (SWT) provide the global aerodynamic information for the verification of the obtained numerical results.