For the problem of hypersonic aircraft inlet compression surface

a reverse design method of constant intensity and isentropic compression surface was proposed firstly based on the investigation of the reverse algorithm of the shock wave theory

then inlet compression surfaces of hypersonic flight vehicle were designed using this method with the flow parameters of inlet exit

next performance analysis and numerical simulation were conducted. The results show that: the reverse design method is effective and time-saving as compared with the traditional method. Theoretical calculation shows that both the geometry parameters and the incoming flow parameters of two compression surfaces are most consistent

the total pressure recovery coefficient of the isentropic compression increases by 6.3% to the constant intensity compression at designed point. The numerical simulation has verified the effectiveness of the proposed method and studied the performance parameters of two compression surfaces under off-design condition

while comparing the internal wave system distribution and airflow uniformity of the inlets under different Mach numbers.