航空学报 > 2014, Vol. 35 Issue (1): 90-96   doi: 10.7527/S1000-6893.2013.0159

采用新型基准流场的高超内收缩进气道试验研究

南向军, 张堃元, 金志光   

  1. 南京航空航天大学 能源与动力学院, 江苏 南京 210016
  • 收稿日期:2013-01-21 修回日期:2013-03-05 出版日期:2014-01-25 发布日期:2013-03-11
  • 通讯作者: 张堃元,Tel.:025-84892200-2100 Email:zkype@nuaa.edu.cn E-mail:zkype@nuaa.edu.cn
  • 作者简介:南向军 男,博士研究生。主要研究方向:内流气体动力学。E-mail:nanxj12@163.com;张堃元 男,硕士,教授,博士生导师。主要研究方向:内流气体动力学。Tel:025-84892200-2100 E-mail:zkype@nuaa.edu.cn;金志光 男,博士,副教授,硕士生导师。主要研究方向:内流气体动力学。E-mail:j_zg77@yahoo.com.cn
  • 基金资助:

    国家自然科学基金(90916029)

Experimental Study of Hypersonic Inward Turning Inlets with Innovative Basic Flowfiled

NAN Xiangjun, ZHANG Kunyuan, JIN Zhiguang   

  1. College of Energy and Power, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
  • Received:2013-01-21 Revised:2013-03-05 Online:2014-01-25 Published:2013-03-11
  • Supported by:

    National Natural Science Foundation of China (90916029)

摘要:

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。

关键词: 内收缩进气道, 高超进气道, 基准流场, 数值模拟, 风洞试验

Abstract:

The innovative basic flowfield with curved centre body has high pressure efficiency and weak reflected shock, so a hypersonic inward turning inlet with rectangular to circular shape transition is designed with this kind of basic flowfield and tested at design point Mach 6.0 in a hypersonic wind tunnel. The pressure distributions on top wall and cowl wall and the parameters 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 characteristics 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 ratio 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.

Key words: inward turning inlet, hypersonic inlet, basic flowfield, numerical simulation, wind tunnel experiment

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