Reynolds averaged Navier-Stokes prediction of shock wave turbulent boundary layer interactions can yield significant error in terms of the size of the separation bubble. In many complex interaction cases, this alters the shock structure and the resulting surface properties. Shock-unsteadiness modification of Sinha et. al. (Physics of Fluids, Vol.15, No.8, 2003) has shown potential in improving prediction in compression corner flows. In this paper, the modification is applied in the simulation of oblique shock wave interacting with a turbulent boundary layer. The flow solution obtained using k-w turbulence model and the implementation of the shock-unsteadiness correction are described in detail. The shock pattern and the surface properties like pressure and skin friction coefficient are compared with experimental data.