Abstract
Three-dimensional transonic flows over the ONERA M6 wing have been computed by many researchers as a benchmark test case. The flow is attractive since it involves $\lambda$-shaped shock on the upper wing at certain Mach numbers. Because of this well-known circumstance, present study is also required of us to study the effect of various turbulent models as well as the computational accuracy through a data exchange program with the Arnold Engineering Development Center (AEDC) of the U.S. Air Force. As a first attempt, the transonic flow at M=0.84, $\alpha=3.06^{\circ}$, Re=11.72E6 is tackled and the CFDS code demonstrates its compatibility with both experimental data and the results of WIND code available in the open domain.