论文部分内容阅读
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 further improve the performance of the hypersonic inlet, a method of inversely designing the entire binary inlet by the specified pressure distribution has been developed. The integrated design of the inlet and the outlet of the inlet with controlled pneumatic parameters has been developed. Software of the port automation design analysis and optimization platform. Preliminary research shows that this design method can be used to obtain the overall performance of the inlet design, the program under the flow Mach 6 throat total pressure recovery coefficient of 0.68, the flow Mach 4 flow coefficient of up to 4 0.77.