The invention belongs to the field of the integrated aerodynamic configuration and propelling flow passage design for air-breathing hypersonic aerial vehicles and relates to an integrated waverider and air inlet configuration based on inward turning basic flowfield and an inverse design method thereof. The method of the invention comprises the main steps of 1, generating an inward turning basic flowfield with given wall parameter distribution by inverse design; 2, generating a front capture tube and air inlet entry capture tube of the integrated waverider forebody air inlet configuration; 3, determining reference points of streamline tracing and osculating axial symmetry process; 4, scaling the basic flowfield proportionally; 5, performing streamline tracing in the proportionally scaled basic flowfield; 6, acquiring compression ramp curves of other waverider forebody air inlets; 7, designing an aircraft body configuration. A waverider forebody with high lift-drag ratio can be designed by the inverse design method provided herein, an air inlet can be inversely designed according to the given wall parameter distribution, pneumatic transition between the waverider forebody and the air inlet can be achieved, and good engineering practicality is achieved.