关键词: 反设计；高超声速进气道；马赫数分布可控；特征线理论；数值模拟

Abstract: Based on the classic theory of two dimensional rotational characteristics，the inverse design methods of the 2-D hypersonic inlet with two curved shock waves and three curved shock waves for generating the given exit Mach number distribution were realized and the Mach number distribution of the inlet rear compression surface is controllable. The results of the numerical study on the two inverse design methods show that both the exit Mach number distribution of inviscid numerical simulation and the exit mainstream Mach number distribution of viscid numerical simulation fit the given target well at the design point. The exit mainstream Mach number distribution keeps high uniformity at the relay point. The above results illustrate that both of the two inverse design methods are correct and feasible. Under the condition of equal capture height，inviscid exit height，design inviscid total pressure recovery coefficient and assembly point flow parameters，the results of viscid simulation show that the two curved shock waves inverse design method wave system is simple and the flow coefficient is 10.2% higher than three curved shock waves at the relay point，while the three curved shock waves inverse design method interior contraction ratio is 17% lower than the former and the total pressure recovery coefficients at the design point and relay point are 2.9% and 2% higher than the former，respectively.

Key words: Inverse design；Hypersonic inlet；Controllable Mach number distribution；Theory of characteristics；Numerical simulation