Abstract: With a fifth-order weighted compact nonlinear scheme(WCNS-E-5),flow field of a 65° delta wing with sharp leading edges at high angles of incidence is simulated.The target is checking WCNS's ability for vortex flow at high angles of incidence and vortex breakdown location with shock-vortex interaction.We focus on sudden jump in breakdown towards apex.Unsteady Reynolds averaged Navier-Stokes(URANS) method is available including a high-order weighted compact nonlinear scheme and an SST turbulence model.It is shown that the high order scheme(WCNS-E-5) with minimum numerical dissipation and could capture discontinuities for high angles of incidence transonic flow of delta wing and the results are matched satisfactorily with experiments.Shock-vortex interaction in transonic freestream explains sudden movement of vortex breakdown as the angle of incidence is increased.

Key words: delta wing, high-order weighted compact nonlinear scheme, high angles of incidence, transonic flows, numerical simulation