Heat reduction and resistance reduction method for hypersonic flight vehicle

The invention discloses a method for reducing heat and drag of a hypersonic aircraft, which comprises the following steps: generating a wall surface normal cold jet flow and/or a wall surface tangential cold jet flow on the wall surface of the hypersonic aircraft, so that a layer of surface cold air film is formed on the boundary layer of the surface of the hypersonic aircraft under the interaction of the cold jet flow and incoming flow. The method is applied to the field of aircraft design, an original gas-solid shearing layer on the surface of the hypersonic aircraft is changed into a gas-gas shearing layer through the surface cold air film generated through interaction of the cold jet flow and the incoming flow, and the speed shearing gradient and the temperature gradient of fluid near the wall face of the hypersonic aircraft are reduced; therefore, the friction resistance and the heat flux density of the boundary layer are reduced, and the heat and resistance reduction of the hypersonic aircraft can be re