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对某典型二元高超声速进气道流场进行了二维数值模拟,研究了抽吸位置及抽吸流量对进气道性能的影响.结果表明:抽吸可以有效地改善进气道起动性能,但不同的抽吸位置改善效果不同.在内压段抽吸时,抽吸流量越大进气道的起动性能改善越明显;外压段抽吸可以有限地改善进气道的起动性能.抽吸孔布置在喉道前压力随马赫数变化较大的区域时,能够实现抽吸流量随来流马赫数的变化自动调节,更好地改善起动性能.对气动性能影响方面,外压段抽吸可以提高进气道的压缩效率,内压段和隔离段抽吸均使压缩效率变小.
A two-dimensional numerical simulation of a typical binary hypersonic inlet flow field was carried out, and the influence of suction position and suction flow on the inlet port performance was studied. The results show that suction can effectively improve the performance of intake port , But the effect of different suction position is different.When the internal pressure section is sucked, the bigger the suction flow is, the more obvious the improvement of the starting performance of the inlet port is; the suction of the external pressure section can improve the starting performance of the inlet port to a limited extent. When the suction hole is arranged in the area where the pre-throat pressure changes greatly with the Mach number, the suction flow rate can be automatically adjusted with the change of the mach number of the flow and the start performance can be better improved. In terms of the aerodynamic performance, Suction can improve the efficiency of the compression of the inlet, and the internal pressure and the suction of the isolation section reduce the compression efficiency.