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为实现高超声速二元进气道前体激波的压缩能力、压缩效率、流量捕获特性和结构长度可控,提出了平面曲线激波逆向设计方法。采用B-Spline曲线控制激波形状。利用有旋特征线法,求解激波的影响域及决定激波的壁面。设计了一凹激波,并对波后流场进行CFD无黏数值模拟,CFD结果和设计结果一致,验证了设计方法的可行性。此外,还设计了直激波、凹激波和凸激波3种激波,并对其在设计点和非设计点处的性能开展了数值研究。在设计点处,分析了激波的压缩比、激波的总压恢复系数、激波压缩区的压升、激波压缩区出口马赫数和流动角随激波控制角的变化规律。在非设计点处,分析了激波压缩区的流量系数和总压恢复系数随攻角和马赫数的变化规律。
In order to realize the compressibility, compression efficiency, flow trapping characteristics and structure length of hypersonic dual inlet precursor shocks, a reverse design method of plane curve shocks was proposed. The B-Spline curve is used to control the shock shape. The spin-eigen-line method is used to solve the influence area of the shock wave and determine the wall of the shock wave. A concave wave was designed and the CFD non-viscous numerical simulation was performed on the wave field. The CFD results are consistent with the design results, which proves the feasibility of the design method. In addition, three kinds of shock wave, straight shock wave, concave shock wave and convex shock wave, are also designed. The performance of the shock wave at design point and non-design point is studied numerically. At the design point, the variation of the shock wave compression ratio, the total pressure recovery coefficient, the pressure rise of the shock compression zone, the Mach number of the shock compression zone and the flow angle with the shock control angle were analyzed. At the non-design point, the variation law of the flow coefficient and the total pressure recovery coefficient with the angle of attack and the Mach number of the shock compression zone are analyzed.