• 首页期刊介绍编委会期刊订阅广告合作联系我们English
  • 选择皮肤:
朱伟,华正旭,王霄.二元弯曲压缩进气道变攻角起动试验[J].航空动力学报,2020,(5):992~999
二元弯曲压缩进气道变攻角起动试验
Variable angle of attack start experiment of 2D curved compression inlet
投稿时间:2019-12-11  
DOI:10.13224/j.cnki.jasp.2020.05.011
中文关键词:  弯曲压缩  进气道起动  反设计  风洞试验  迟滞现象
英文关键词:curved compression  inlet start  reverse design  wind tunnel experiment  hysteresis phenomenon
基金项目:
作者单位
朱伟 College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China
Shenyang Aircraft Design and Research Institute,Aviation Industry Corporation of China Limited,Shenyang 110035,China
 
华正旭 Shenyang Aircraft Design and Research Institute,Aviation Industry Corporation of China Limited,Shenyang 110035,China
 
王霄 College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China
Shenyang Aircraft Design and Research Institute,Aviation Industry Corporation of China Limited,Shenyang 110035,China
 
摘要点击次数: 115
全文下载次数: 154
中文摘要:
      开展了内外压缩型面可控的弯曲压缩进气道反设计方法研究,并针对设计的二元弯曲压缩进气道进行了不同马赫数下变攻角起动数值仿真及试验研究,获得了进气道起动攻角迟滞环,仿真与试验得到的不起动/自起动攻角、出口流场以及压力分布吻合良好,同时试验结果也表明设计的弯曲压缩进气道具有较高的综合气动特性,设计点Ma=4、α=3°抗反压能力70倍来流压力以上,总压恢复系数在0.5以上。
英文摘要:
      The reverse design method of curved compression inlet with controllable internal and external compression surfaces was studied, the numerical simulation and experimental study of the designed 2D curved compression inlet starting with varying angle of attack at different Mach numbers were carried out, and the hysteresis loop of the inlet starting angle of attack was obtained. Simulation and experiment indicated that unstarting/self-starting angle of attack, the outflow field and pressure distribution coincided well, and the experiment results also showed that curved compression inlet had high comprehensive aerodynamic characteristics; at design points Ma=4, α=3° back pressure resistance ability was more than 70 times of inflow pressure, total pressure recovery coefficient was above 0.5.
查看全文  查看/发表评论  下载PDF阅读器
关闭
.