The flow response hysteresis in a mixed-compression supersonic inlet's throttling/unthrottling process is unconducive to its practical engineering applications. To suppress such hysteresis, herein, a flow control method based on a distributed bleed system in the inlet's internal contraction part was proposed and applied to a rectangular supersonic inlet with a designed Mach number of 4.0 and an internal contraction ratio of 1.5. All tests were conducted in a supersonic wind tunnel at a freestream Mach number of 2.9, and the relevant test data were obtained using the high-speed schlieren and dynamic pressure measurement systems. The results indicate that the distributed bleed system improved the uncontrolled inlet's unstart throttling ratio from 43.8% to 47.3% and the restart throttling ratio from 29.4% to 47.1%, and it essentially eliminated the flow response hysteresis during the throttling/unthrottling process. Moreover, the hysteresis mechanism of the uncontrolled inlet, dominated by the separation-induced flow structures in the internal contraction part, was investigated to help elucidate the targeted control mechanism of the bleed system that suppresses the hysteresis. Finally, the specific flow phenomena in the oscillation of the controlled inlet were examined to study the bleed system's impact on the unsteady flowfield, including the coupled flow of the mainstream with the bleed system and complex wave motion structures.

混合压缩超音速进气道节流/非节流过程中的流动响应滞后不利于其实际工程应用。为了抑制这种滞后现象，本文提出了一种基于进气道内收缩部分分布泄放系统的流量控制方法，并将其应用于设计马赫数为4.0、内收缩比为1.5的矩形超音速进气道。所有测试均在超音速风洞中进行，自由流马赫数为2.9，相关测试数据采用高速纹影和动态压力测量系统获得。结果表明，分布式引气系统将非受控进口的未启动节流率从43.8%提高到47.3%，将重启节流率从29.4%提高到47.1%，它基本上消除了节流/非节流过程中的流量响应滞后。此外，研究了由内部收缩部分中的分离引起的流动结构主导的不受控入口的滞后机制，以帮助阐明抑制滞后的排放系统的目标控制机制。最后，研究了受控入口振荡中的具体流动现象，研究了放气系统对非定常流场的影响，包括主流与放气系统的耦合流动和复杂的波动结构。进行了调查以帮助阐明抑制滞后的排放系统的目标控制机制。最后，研究了受控入口振荡中的具体流动现象，研究了放气系统对非定常流场的影响，包括主流与放气系统的耦合流动和复杂的波动结构。进行了调查以帮助阐明抑制滞后的排放系统的目标控制机制。最后，研究了受控入口振荡中的具体流动现象，研究了放气系统对非定常流场的影响，包括主流与放气系统的耦合流动和复杂的波动结构。