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中文摘要：
采用非定常数值仿真方法研究了进气道自起动过程中流动的非定常特性,分析了内压段构型对非定常流动特性的影响。研究结果表明：进气道自起动过程中流动特性受内压段构型与来流条件影响。内压段压缩面肩部曲率半径越大,内压段面积收缩越缓,越易出现流场振荡现象,流场振荡越剧烈;型面设计参数β≤33°,能够避免流场振荡现象出现。合理设计进气道内压段型面能够控制自起动过程中流动的非定常特性。自起动过程中,流场出现振荡时随着来流马赫数增大流动依次经历不振荡状态→振荡状态→不振荡状态→起动状态,且流场振荡频率逐渐下降;对于未发生流场振荡的进气道,随着来流马赫数增大进气道依次经历硬不起动状态→软不起动状态→起动状态。
英文摘要：
The unsteady flow characteristics of hypersonic inlet and the influence of the internal compression duct geometry on them during self-starting are studied with the unsteady numerical simulation.The results show that the unsteady flow characteristics are influenced by the internal compression duct geometry and the free stream condition.The curvature radius of the shoulder of internal compression surface is larger,the contraction rate of internal compression duct is slower,and the flow oscillation occurs easily with stronger oscillation intension.However,the flow oscillation disappears when the curvature radius of the shoulder is small enough（the geometry parameterβ≤33°）.If the flow oscillation occurs during inlet self-starting,the oscillation frequency decreases and the no oscillation,oscillation,no oscillation and started mode appears one by one with the increase of free stream Mach number.And for the case that the flow oscillation does not occur during self-starting,the inlet suffers the hard-unstarted mode,soft-unstarted mode and started mode in sequence with the free-stream Mach number increasing.
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