The interaction between a shock wave and a turbulent boundary layer, commonly known as shock-wave/turbulent boundary layer interaction (SWTBLI), is a critical factor that affects the performance of hypersonic vehicles and their propulsion systems. This phenomenon has significant implications for the aerodynamic characteristics, structural integrity, and propulsion efficiency of hypersonic vehicles [1]. The SWTBLIs at supersonic flow regime have been extensively studied using direct and large-eddy simulations. However, a hypersonic SWTBLI with a strong interaction intensity and large flow separations are relatively less studied. The interaction between an oblique shock-waves and a flat-plate turbulent boundary layer at a freestream Mach number of 5 is studied by using a direct-numerical simulation (DNS) approach based on a high-order finite-difference solver ASTR code. By appropriately correcting the deflection angle of the impinging shock-wave, good agreements with experimental data [2] are achieved (see Figure 1). Compared with most previous DNS data, the studied hypersonic shock-wave/turbulent boundary layer interaction has a relatively large interaction strength, leading to high recovery skin-friction, large amplification ratio of Reynolds stress, and strong wall pressure fluctuations. The DNS data are analysed with a particular focus on the characteristics of the shear layer generated by the interaction and its impact on turbulence statistics. The spatial evolution of the shear layer is characterised with four phases, namely the initial formation phase, the stabilisation phase, the reattaching phase, and the diffusion and dissipation phase. The four-phase evolution of the shear layer has clear impacts on Reynold stress, turbulence kinetic energy transport characteristics, and instantaneous turbulence structures.