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在马赫5、正8°攻角状态对收缩比为6.9的带楔形前体的矩形转圆形内收缩进气道进行了风洞试验和数值模拟,研究了该进气道无放气及有放气时在风洞中的启动特性。结果表明,无放气状态该进气道在风洞中并不能顺利启动,不启动状态进气道顶板上存在较大分离区,分离激波被推出内压缩段,此时总压恢复仅为0.378,增压比为54.1,出口马赫数为1.48。通过在内压段的顶板上激波附面层相互作用区域放气后,该进气道可在风洞中正常启动。启动后总压恢复为0.558,增压比减小至44.9,出口马赫数为1.84,放气量约为唇口封闭处截面流量的1.2%。以上研究表明,放气可有效改善内收缩进气道的启动性能,启动后放气量较小,总体性能较优。
Wind tunnel tests and numerical simulations were carried out on a rectangularly-rounded circularly contracted inlet with a wedge precursor at a Mach 5 and an angle of attack of 8 ° with a contraction ratio of 6.9. It was found that the inlet has no deflation and Ventilation in the wind tunnel in the starting characteristics. The results show that in the non-deflated state, the inlet does not start smoothly in the wind tunnel. In the non-activated state, there is a large separation area on the top of the inlet duct and the separation shock is pushed out of the inner compression section. At this moment, the total pressure recovery is only 0.378, supercharger ratio of 54.1, the export Mach number 1.48. The air inlet can be normally started in the wind tunnel by deflating the area of interaction of the shock wave cladding on the roof of the internal pressure section. After the start of the total pressure recovery was 0.558, turbocharger ratio decreased to 44.9, the Mach number for the exit 1.84, deflated about lip cross-sectional area of 1.2%. The above studies show that deflation can effectively improve the performance of the contraction of the inlet port, deflation after start-up smaller overall performance better.