Integrated aerodynamic layout method for hypersonic aircraft forebody, air inlet duct and supporting plate

The invention discloses an integrated aerodynamic layout method for a hypersonic aircraft forebody, an air inlet duct and a supporting plate. A combined standard flow field combining an inner core flow field, an isentropic flow field and a truncation Busemann flow field is adopted, a streamline tracer technology is used, based on a free incoming flow capture size and a downstream combustion chamber inlet size given by the overall configuration of an aircraft, a forebody compression face, an air inlet duct compression face and a supporting plate lateral compression face are constructed with traced streamline clusters starting from an outlet of the downstream air inlet duct, and the forebody, the air inlet duct and the supporting plate are smoothly connected to achieve integrated aerodynamic layout configuration. The three-dimensional space structure of the aircraft forebody and the air inlet duct is improved, the disturbing influence of the supporting plate is eliminated in a side face compression mode, adverse factors are converted into favorable compensation, the forebody, the air inlet duct and the supporting plate are reasonably laid out from the space three-dimension perspective, and flowing is kept to be isentropic flowing to the maximum extent, which is beneficial for reducing flowing loss and improving overall performance of the aircraft.