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针对一种马赫数分布可控的二元高超弯曲压缩面进行参数化研究,获得其设计参数对压缩面性能的影响规律,在此基础上建立多项式响应面代理模型并进行多目标优化,基于优化结果设计了二元弯曲激波进气道,并与同等约束条件下的三楔进气道进行比较。结果表明:压缩面初始压缩角θ与马赫数梯度函数中的设计参数md1,C对压缩面性能影响最为显著;Ma∞=4.0时弯曲激波进气道流量系数达0.769,与三楔进气道相比,在Ma∞=4~7工作范围内的流量捕获能力相当,但其喉道、出口截面的总压恢复系数均高于三楔进气道,在Ma∞=4,6,7工况下,喉道截面总压恢复分别有6.5%,8.4%和10.7%的提高。
Aiming at a parametric study of a biconcave supercompression compression plane with controlled Mach number distribution, the influence of its design parameters on the performance of the compression plane is obtained. Based on this, a polynomial response surface proxy model is established and multi-objective optimization is performed. The results of the design of the binary curved shock inlet, and with the same constraints compared to the three wedge inlet. The results show that the compressive surface initial compression angle θ and the design parameters md1 and C of the Mach number gradient function have the most significant effect on the compressibility surface. The flow coefficient of the curved shock inlet reaches 0.769 when Ma∞ = 4.0, The total pressure recovery coefficient of the throat and outlet section is higher than that of the triple wedge inlet in Ma∞ = 4 ~ 7 working range, Operating conditions, the throat section total pressure recovery were 6.5%, 8.4% and 10.7% increase.