出口马赫数分布可控的二元高超进气道双重反设计

Double Inverse Design of 2-D Hypersonic Inlet with Controllable Exit Mach Number Distribution

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

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

摘要:

在出口马赫数分布预先给定的前提下，利用二维有旋特征线理论实现了压缩面马赫数分布可控的两弯曲激波和三弯曲激波高超二元进气道反设计。数值计算结果表明，设计点时，无粘条件下两种反设计方法均能实现预设出口马赫数分布，有粘条件下反设计的进气道出口主流区马赫数分布与预设分布吻合较好，接力点时出口主流区马赫数仍然保持较好的均匀性。以上结果说明这两种反设计方法均是正确可行的。设计条件下，在捕获高度、无粘出口高度、设计无粘总压恢复系数和装配点处流动参数均相同时，两弯曲激波反设计方法波系简单、有粘接力点流量系数较三弯曲激波高10.2%；三弯曲激波反设计方法有粘时内收缩比较前者小17%，设计点和接力点时总压恢复系数分别较前者高2.9%和2%。

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.