Design method of hypersonic integrated air inlet channel with given precursor shape

The invention belongs to the field of hypersonic speed air inlet channel design, and particularly relates to a design method for a hypersonic speed integrated air inlet channel with a given precursor shape. Comprising the following steps: according to a given aircraft forebody shape, fitting forebody front edge shock waves as shock wave molded lines through numerical values, selecting a proper axial symmetry reference flow field, then carrying out air inlet spanwise design according to an osculating principle, carrying out flow direction design by utilizing a streamline tracking technology, and carrying out geometric splicing on the obtained air inlet molded surface and the aircraft forebody, so as to obtain the aircraft forebody. The air inlet channel structure meeting the requirement of the hypersonic speed precursor can be obtained. According to the method, the front edge line of the aircraft forebody is attached to the front edge line of the air inlet channel, under the design working condition, shock wav