Axisymmetric basic flowfields with controlled pressure gradient used for hypersonic inward turning inlets were investigated using the rotational method of characteristics.In combination with streamline tracing technique

a circular inward turning inlet with the law of constant pressure gradient was designed and numerically simulated.Results show that the inward turning inlet could maintain the same law of pressure rise as its basic flowfield.Through study of the three laws of wall pressure rise

pressure gradient increase

steadiness and decrease

it's found the inlet with the first law of pressure rise has the maximum compression efficiency

and the inlet with the third law of pressure rise has the lowest compression efficiency.In addition

we can get good internal and external compression assignment by adjusting the law of pressure rise

contributing to make this type of inlet operate well over a large wide range of Mach number.