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Parameterization and optimization design of a two-dimensional axisymmetric hypersonic inlet
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ( IF 1.1 ) Pub Date : 2021-06-29 , DOI: 10.1177/09544100211029535
Shangcheng Xu 1 , Yi Wang 1 , Zhenguo Wang 1 , Xiaoqiang Fan 1 , Bing Xiong 1
Affiliation  

Optimization method, as a promising way to improve inlet aerodynamic performance, has received increasing attention. The present research is undertaken to design a two-dimensional axisymmetric hypersonic inlet using parametric optimization. The inlet configuration is parameterized and optimized in consideration of total pressure recovery and starting performance. A Pareto front is obtained by solving the multi-objective optimization problem. Then, the flow structures of the optimized inlets are analyzed and the starting performances are evaluated. Results show that the total pressure loss mainly occurs in the internal contraction section, especially near the inlet entrance, and therefore the total pressure recovery coefficient can be greatly improved by decreasing external compression. As a result, the guidance for designing high-performance inlets is concluded. Besides, it is found that as the internal contraction ratio increases, the inlet starting ability becomes worse, which attributes to the larger separation bubble at the inlet entrance. Finally, the total pressure recovery coefficient and the starting Mach number of the optimized inlets are obtained, which can be a reference for engineering design.



中文翻译:

二维轴对称高超声速进气道参数化及优化设计

优化方法作为一种提高进气道气动性能的有前景的方法,越来越受到重视。本研究旨在使用参数优化设计二维轴对称高超声速进气道。考虑到总压力恢复和启动性能,对入口配置进行了参数化和优化。帕累托前沿是通过解决多目标优化问题获得的。然后,对优化后的进气口的流动结构进行了分析,并对启动性能进行了评估。结果表明,全压损失主要发生在内收缩段,尤其是入口附近,因此通过降低外压可以大大提高总压恢复系数。因此,对设计高性能进气道的指导进行了总结。此外,发现随着内部收缩率的增加,入口启动能力变差,这归因于入口入口处较大的分离气泡。最后得到优化后的进气道总压恢复系数和起始马赫数,可为工程设计提供参考。

更新日期:2021-06-30
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