采用新型基准流场的高超内收缩进气道试验研究

Experimental Study of Hypersonic Inward Turning Inlets with Innovative Basic Flowfiled

由于新型变中心体基准流场具有压缩效率高、反射激波弱的优点,采用该基准流场设计了矩形转圆形内收缩进气道,在设计点马赫数Ma=6.0进行了风洞试验研究。试验中得到了进气道压缩面的沿程压力分布、隔离段出口皮托压分布等参数。通过和数值模拟对比分析,结果表明:进气道外压段的压力分布明显具有先增大后减小的特征,内压段的压力分布具有两级爬升的特点,且压升较小,流场结构较好。由于内压段流场激波强度弱,进气道总压恢复系数较高,达0.518,并产生了52倍的增压比,其抗反压能力在144倍以上。试验研究表明,采用新型变中心体基准流场能改善矩形转圆形内收缩进气道的内压段流场及隔离段流场,并能有效提高进气道的总压恢复系数。

The innovative basic flowfield with curved centre a hypersonic inward turning inlet with rectangular to circular tested at design point Mach 6.0 in a hypersonic wind tunnel. body has high pressure efficiency and weak reflected shock, so shape transition is designed with this kind of basic flowfield and The pressure distributions on top wall and cowl wall and the pa- rameters distribution at isolator exit is obtained in this experiment. The results of experiment and numerical simulation turn out the pressure gradient increasing at initial part, then deceasing, and the pressure distribution in internal part has charac-teristics of two-pressure-rise, and the pressure rise is low, so the flowfield of internal part is good. Because the shock in the internal part of inlet is weak, the inlet has high pressure recovery coefficient, about 0. 518, and generates a compression ra-tio of 52. The critical back pressure ratio of this inlet is above 144. The innovative basic flowfield can improve the flowfield of internal part and isolator and increase the pressure recovery of the inlet with rectangular to circular shape transition.