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针对二元定几何混压式超声速进气道低马赫数时流量系数低加速性能差的问题,提出了一种新的泄流槽流场控制概念,并通过数值仿真,揭示了泄流槽控制激波结构机理及其主要几何参数对进气道性能的影响规律.研究结果表明:采用该流场控制方案可通过泄流槽入口处的波系结构使进气道在低于设计马赫数时的出口总压恢复系数和流量系数相对于原型方案均得到明显提高,而在设计点关闭泄流槽后进气道的性能与原型进气道基本相当,这对改善冲压发动机在低马赫数转级后的加速性能是有利的.
In order to solve the problem of low flow rate and low accelerating performance at low Mach number of binary mixed geometry supersonic gas inlet, a new concept of flow field control of spillway is proposed. Numerical simulation shows that the control of spillway Shock wave structure and its main geometric parameters on the performance of the inlet.Research results show that the flow field control scheme can make the intake passage less than the design Mach number through the wave structure at the entrance of the discharge slot Of the total outlet pressure recovery coefficient and flow coefficient relative to the prototype program have been significantly improved, and the design of the closure of the discharge port after the inlet port performance is basically the same as the prototype inlet, which improves the stamping engine at low Mach number turn Acceleration performance after the stage is advantageous.