中文摘要：

在马赫5、正8°攻角状态对收缩比为6.9的带楔形前体的矩形转圆形内收缩进气道进行了风洞试验和数值模拟,研究了该进气道无放气及有放气时在风洞中的启动特性。结果表明,无放气状态该进气道在风洞中并不能顺利启动,不启动状态进气道顶板上存在较大分离区,分离激波被推出内压缩段,此时总压恢复仅为0.378,增压比为54.1,出口马赫数为1.48。通过在内压段的顶板上激波附面层相互作用区域放气后,该进气道可在风洞中正常启动。启动后总压恢复为0.558,增压比减小至44.9,出口马赫数为1.84,放气量约为唇口封闭处截面流量的1.2%。以上研究表明,放气可有效改善内收缩进气道的启动性能,启动后放气量较小,总体性能较优。

英文摘要：

A hypersonic inward turning inlet with rectangular to circular shape transition integrated to a wedge fore body,whose total contraction ratio is 6.9,is investigated at Ma5,attack angle 8° with numerical simulation and wind tunnel experiment.The starting performance is studied with and without bleed on top wall in the internal compression section.The results indicate that the inlet can not start without bleed.There is large separation bubble on the top wall of the external compression section.When the inlet unstarts,the total pressure recovery,the compression ratio and the Mach number of isolator exit are 0.378,54.1 and 1.48,respectively.When the bleed slots in the shock wave and the boundary layer interact zone of top wall are open,the inlet starts in the experiment.Then the total pressure recovery,the compression ratio and the Mach number of isolator exit are 0.558,44,9 and 1.84,respectively,with about 1.2% of the flow entering the cowl closure section lost.The test turns out that the inlet can start with small amount of gas lost and has good performance if it starts.