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采用压力梯度先增大后减小压升规律轴对称基准流场,结合流线追踪及截面渐变技术设计了矩形转圆形内收缩进气道模型,并采用4°斜楔模拟飞行器前体,对前体、进气道一体化模型进行了数值模拟和风洞试验,初步得到了该进气道的流场结构及总体性能。设计点和接力点的数值模拟结果表明该进气道可在马赫数Ma=4～6状态下正常工作,且具有良好的总体性能。在设计点Ma=6、正4°攻角状态进行的风洞试验表明,该进气道增压比为41.2,总压恢复达0.45,至少可抵抗200倍来流静压的反压。
In this paper, the rectangular rotating circular internal contraction inlet model was designed by using the pressure gradient first increasing and then decreasing the pressure increasing regular axisymmetric reference flow field. Combined with the flow line tracing and section gradient technology, the 4 ° wedge was used to simulate the precursor of aircraft, Numerical simulation and wind tunnel test were carried out for precursor and inlet integrated models, and the flow field structure and overall performance of the inlet were obtained. The numerical simulation results of the design point and the relay point show that the air intake can work normally under Mach number Ma = 4 ~ 6, and has good overall performance. Wind tunnel tests conducted at the design point of Ma = 6 and at a 4 ° angle of attack show that the intake manifold pressurization ratio is 41.2 and the total pressure recovery is 0.45, at least 200 times the backpressure of the hydrostatic pressure.