Overflow port cooling structure of scramjet engine

The invention provides a scramjet engine overflow port cooling structure which comprises an inclined front edge arranged in front of a V-like front edge of an overflow port, an inclined front edge to overflow port transition chamfer and an overflow port structure, and the inclined front edge, the inclined front edge to overflow port transition chamfer and the overflow port structure are sequentially connected. The overflow port structure comprises a straight section and a C-shaped port. Oblique front edge detached shock waves are hit to an inlet of the overflow port to form a shock wave interference area, a flow field develops towards the downstream of the overflow port, and meanwhile flow field energy overflows towards the two sides, so that the high heat flow gathering phenomenon on the wall face near the overflow port is reduced. The aerodynamic configuration designed by the invention can effectively reduce the thermal load of the aircraft under the high Mach number flight condition under the condition of