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为了改善高超声速进气道在低马赫数下的自起动能力,提出了一种在进气道内利用不起动时诱导激波前后静压差开设回流通道的流场控制概念,对其改善流场特性的机理及回流通道典型几何参数对进气道流场特性和气动性能的影响进行了分析,获得了回流通道典型几何参数对进气道自起动性能的影响规律,并与原型面进气道性能进行对比分析。结果表明:回流通道使进气道自起动马赫数由Ma=4.7降低至Ma=3.6,进气道工作马赫数范围得到显著拓宽;回流通道进口位置对进气道自起动马赫数存在较大影响,但自起动马赫数几乎不随回流通道出口位置、回流通道宽度(b≥8mm)而改变;在低马赫数时,回流通道对进气道不起动流场有明显改善。而高马赫数下回流通道对进气道性能几乎不产生影响,保证了高马赫数下进气道的性能。
In order to improve the self-starting ability of the hypersonic inlet at low Mach number, a new concept of flow field control is proposed, which uses the static pressure difference before and after the shock wave is induced in the intake passage to improve the flow field The characteristics of the mechanism and the typical geometric parameters of the return channel on the inlet flow field characteristics and aerodynamic performance were analyzed to obtain the typical geometric parameters of the return channel on the inlet self-starting performance, and with the prototype surface inlet Performance comparative analysis. The results show that the recirculation channel reduces the self-starting Mach number of the air intake from Ma = 4.7 to Ma = 3.6, and the working Mach number range is significantly widened. The inlet position of the recirculation channel has a great influence on the self-starting Mach number , But the self-starting Mach number almost does not change with the position of the outlet of the return passage and the width of the return passage (b≥8mm); at low Mach number, the return passage can not significantly improve the inlet non-actuating flow field. The high Mach number of return passage on the inlet performance almost no impact, to ensure high Mach number inlet performance.