Direct numerical simulation of a supersonic compression corner

Direct numerical simulation (DNS) of a supersonic compression corner has been performed using a turbulent-library based inflow generation method, which means adding turbulence fluctuations from preexisted turbulence library files on the current inflow boundary. Illustration of application of such method is given. Physically turbulence boundary layer (TBL) can be obtained after a short distance 'transition' process. Qualitative results show that the current numerical simulation is able to obtain the fully developed turbulent boundary layer in the downstream and capture the shock structure well. The accuracy and reliability of current method is proved by the comparison of quantified results between DNS and experimental data. The interaction between the shock wave and the turbulent boundary layer near the corner has been analysed. Turbulent intensity is enhanced passed through the shock and the mean velocity profiles in the separation zone have suffered significant changes.