Shock/turbulent boundary layer interaction is a focus of active research because of its relevance to practical applications like scramjet inlets. Flow separation due to shock waves in the inlet duct can significantly deteriorate the performance. Computational fluid dynamic prediction of shock/turbulent boundary layer interactions are often limited by the accuracy of the turbulence models. Traditional models like k − ǫ, k −ω and Spalart-Allmaras cannot predict the correct level of turbulent kinetic energy k downstream of a shock wave. In-depth study of the equations governing k-amplification at a shock reveals new physical mechanisms caused by the coupling of shock motion with the turbulent velocity fluctuations. Incorporating this additional term in the turbulence models results in significant improvement in their predictions. The new models are validated against experimental data available for canonical shock/turbulent boundary layer interactions. In-house CFD codes with advanced turbulence models are then used to investigate realistic scramjet inlet flowfields. Geometric details and three-dimensionality of a reallife configuration result in highly complex shock/turbulent boundary layer interactions. To understand such flow fields and predict them accurately is the focus of on-going research.