以二维轴对称高超声速进气道为研究对象,研究唇口角对进气道总压恢复性能、阻力性能和起动性能的影响,开展多目标考虑下唇口角设计。首先,采用三阶准均匀B样条对唇罩进行参数化设计,获得具有不同唇口角的进气道构型。然后基于数值仿真方法研究唇口角对进气道总压恢复性能、阻力性能和起动性能的影响。结果表明,存在一个最佳唇口角使进气道总压恢复性能最佳。分析发现唇口角过小时入口处会形成强烈唇口激波,唇口角过大时内收缩段会形成汇聚激波,二者均会造成严重总压损失。在阻力性能研究中发现通过减小唇口角,可有效减小内外唇罩阻力,但压缩侧壁面阻力因唇口激波强度增加而增大,在三者共同作用下进气道总阻力随唇口角增大表现出先减小后增大的规律。在唇口角对起动性能的影响研究中同样发现存在一个最佳唇口角使进气道起动性能最佳。唇口角过小时大尺度分离区难以被吞入,唇口角过大时分离区在内收缩段形成稳定驻留,两者均不利于进气道起动。最后,分析了不同内收缩比下进气道唇口角对总压恢复性能、阻力性能和起动性能的影响,并对多目标考虑下最优唇口角设计展开研究。结果表明使总压恢复性能、阻力性能和起动性能分别最佳的唇口角并不重合,但总体而言三者相差不大,通过唇口角设计可使进气道同时达到较好的总压恢复性能、阻力特性和起动性能。
The effects of the cowl lip angle on total pressure recovery, drag performance and starting ability of a two-dimensional axisymmetric hypersonic inlet are investigated and a cowl lip angle is designed. The configuration of the cowl is first parameterized by a 3rd B-spline, and various inlet configurations with different cowl lip angles are obtained. Numerical simulation is then conducted to investigate the effect of the cowl lip angle on inlet total pressure recovery performance, drag performance, as well as starting ability. Results show the existence of an optimal cowl lip angle for the inlet to achieve the best total pressure recovery performance. It is found that a strong cowl shock stands at the entrance of the inlet with a small cowl lip angle, a convergent shock stands in the internal contraction region of the inlet with a large cowl lip angle, and both will cause serious total pressure loss. In the study of drag performance, the drags of both the inside and outside cowls can be effectively reduced by decreasing the cowl lip angle, while the drag of the compression wall increases due to the shock/boundary layer interaction. Affected by the three factors, the total drag decreases initially and then increases with the rise of the cowl lip angle. An optimal cowl lip angle also exists to achieve the best starting performance for the inlet with the same internal contraction ratio. In addition, when the cowl lip angle is too small, the large scale separation bubble of the unstarted inlet is hard to be swallowed, while the separation bubble forms a stable residence in the internal contraction region when the cowl lip angle is too large. Finally, the effect of the cowl lip angle on aerodynamic performance of inlets with various internal contraction ratios is explored and the design of the optimal cowl lip angle is discussed. Results show that the cowl lip angles to achieve the best total pressure recovery, the minimum drag and the best starting ability, respectively, are not the same; however, generally speaking, the differences among them are insignificant. Therefore, the researched inlet can achieve good total pressure recovery performance, drag characteristic, and starting ability simultaneously with a reasonable cowl lip angle.
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