基于壁面压力分布的二元高超声速弯曲激波压缩进气道反设计与优化方法

Reverse Design and Optimization of 2D Hypersonic Curved Shock Compression Inlet Based on Given Wall Pressure Distribution

为进一步提高高超声速进气道的性能,发展了通过指定压力分布规律来反设计整个二元进气道的方法,实现了气动参数可控的进气道内外压缩一体化设计,建立了基于Isight软件的进气道自动化设计分析和优化平台。初步的研究表明,使用此设计方法,能够得到综合性能优秀的进气道设计方案,该方案在来流马赫数6下喉道总压恢复系数为0.68,在来流马赫数4时流量系数达0.77。

In order to improve the performance of hypersonic inlet, a method of reverse designing two- dimensional hypersonic inlet according to specified wall pressure distribution was developed. An integrated designing method of inlet external and internal compression with controllable gas-dynamic parameters was a- chieved, and an automatic designing, simulation and optimization system of hypersonic inlet was created based on commercial software Isight. The preliminary study shows that inlet with good comprehensive performance could be obtained in this way. The optimized inlet system has total pressure recovery of 0.68 at the throat section under Mach 6, and mass flow capture of 0.77 under Mach 4.