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基于反正切马赫数分布的弥散反射激波中心体轴对称基准流场,设计了方转圆内收缩进气道,并对其进行风洞试验和数值仿真研究,获得该进气道非设计点(Ma=5.0和Ma=7.0)的工作特性和自起动特性。试验结果表明:进气道顶板压力分布具有反正切曲线特征,出口涡流区小且总体性能优良。Ma=5.0和Ma=7.0时出口总压恢复系数分别为0.647和0.443,对应的增压比分别为20.0和32.7。Ma=5.0时,进气道不但可以捕获约90%的自由来流,而且能够自起动(内收缩比高于Kantrowitz限制),下临界反压为64倍来流静压,对应的出口马赫数和总压恢复系数分别为1.32和0.409。上述结果表明,本文设计方法可以获得高性能的矩形转圆内收缩进气道。
Based on the axisymmetric reference flow field of the central axis of dispersion reflection shock centered in arc tangent Mach number distribution, an inwardly convergent inlet was designed and tested by wind tunnel and numerical simulation. The non-design point (Ma = 5.0 and Ma = 7.0) operating characteristics and self-starting characteristics. The experimental results show that the inlet pressure distribution has the arc-tangent curve, the exit vortex area is small and the overall performance is excellent. At Ma = 5.0 and Ma = 7.0, the total outlet pressure recovery coefficients were 0.647 and 0.443, respectively, corresponding to 20.0 and 32.7 respectively. At Ma = 5.0, the port not only captures approximately 90% of the free flow but also self-starts (internal systolic ratio above the Kantrowitz limit), the lower critical back pressure is 64 times the hydrostatic pressure, the corresponding outlet Mach number And total pressure recovery factors were 1.32 and 0.409, respectively. The above results show that the design method of this paper can obtain high-performance rectangular round converging inlet.