摘要
首先对澳大利亚HyShot计划进气道模型进行了数值模拟,得到了设计状态及非设计状态下的流场特征,以及进气道性能随来流马赫数的变化规律.根据分析,提出了在二元高超声速进气道内压段开设溢流槽的设计思路,设计了工作马赫数范围为4.0～6.0的二元高超声速进气道,并给出了通过抬高或降低原设计槽口高度得到的两种新的开槽方案进气道的物理模型.通过数值模拟,结果表明:溢流槽有效改善了进气道的性能,拓宽了进气道的工作范围,槽口高度的不同对进气道性能有相当大的影响.
The inlet model of HyShot program was simulated.The flow fields of the HyShot inlet under the design and non-undersign conditions,as well as the inlet＇s performance with the variation of Mach numbers were obtained.The design for slotting at two-dimensional hypersonic inlet was brought forward hereby and a two-dimensional hypersonic inlet working at Mach number 4.0～6.0 was designed.Furthermore,two new inlet models were designed by raising or lowering the height of the original slot.By comparing the simulation results of these three inlet models and the inlet without slot under different Mach numbers,it shows that the spillage slot improves the performance of inlet effectively and expands the inlet＇s operating region.It can also be found that different slot heights would fairly affect the performance of inlet.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第7期1573-1580,共8页
Journal of Aerospace Power
