Abstract: High order accuracy numerical simulations for flows of high lift trapezoidal wing configuration were performed by solving NavierStokes equation together with SST twoequation turbulence model. In the study, WCNS-E-5 scheme was utilized in the discretization of convection terms, while 6th order central difference scheme for viscous term. Grid convergence result was obtained, which was in good agreement with test data, and WCNS scheme was less dependent on mesh density than 2nd order scheme. Compared with other computational results obtained by typical CFD solvers, both the force coefficients and the surface pressure distributions given in this paper shown better accordance with the test data, and more reasonable prediction of flow structure near stalling was obtained. As revealed from these results, WCNS scheme took higher accuracy order and was more suitable for simulation of flow around high lift configurations than 2nd order scheme. The capability and the robustness of the program to simulate complex high lift configurations were confirmed.