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为探索利用射流技术降低进气道起动马赫数的可行性,对二元高超声速进气道二维流场进行了数值模拟,通过对比不同工况的流场结构、流量系数及总压恢复系数,分析了射流对高超声速进气道的作用效果,并研究了射流速度、压强及倾角对进气道起动性能的影响。分析结果表明:施加射流,激波与进气道边界层原有干扰形式发生改变,是降低进气道起动马赫数的主要原因。研究还表明,增大射流速度利于提高控制效果,但持续增大射流速度,会造成隔离段反压升高,并且这一现象与射流压强相关,降低射流压强能使进气道起动的射流速度区间扩大,同时在不同射流倾角下,上述规律表现一致。该研究揭示了进气道起动能力随射流参数变化的系统性规律,可用于指导工程设计及优化。
In order to explore the feasibility of using jet technology to reduce the starting Mach number of inlet, two-dimensional hypersonic two-dimensional flow field of inlet was numerically simulated. By comparing the flow field structure, flow coefficient and total pressure recovery coefficient The effects of jet on the hypersonic inlet were analyzed. The effects of jet velocity, pressure and inclination on the performance of the inlet were also studied. The analysis results show that the original interference pattern of impinging jet, shock wave and inlet boundary layer is changed, which is the main reason to reduce the starting Mach number of inlet port. The research also shows that increasing the jet velocity will improve the control effect. However, increasing the jet velocity continuously will result in the increase of backpressure in the isolation section, and this phenomenon is related to the jet pressure. Reducing the jet pressure can make the jet velocity of the inlet port start The interval expanded, at the same time in different jet inclination, the above law consistent. The study reveals the systemic law of the inlet starting ability with the jet parameters changes, which can be used to guide the engineering design and optimization.