Abstract: The flow over a hypersonic jaws inlet was experimentally and numerically studied. Flow characteristics in hypersonic jaws inlets have been presented by theoretic, experimental and numerical methods. The experimental method and technology of highcontractionratio jaws inlet in hypersonic wind tunnel was given to acquire the experimental data of starting inlet. Numerical results demonstrated that a pair of threedimensional vortical structures for mixing enhancement was formed as a result of the pitch and yaw shock waves/boundarylayer interactions, and the mechanism for the 3D flow structure was explained by analyzing the streamlines distributions in boundary layer around the cowl.