大型低速二元风洞侧壁边界层控制及对单段翼型实验结果的影响  

The Sidewall Boundary Layer Control for Larger 2 D Low Speed Wind Tunnel and Its Effect on Airfoil Experiment Results

作　　者：周瑞兴[1] 上官云信[1] 郗忠祥[1] 胡玉贵[1] 高永卫[1] 张理[1] 

机构地区：[1]西北工业大学

出　　处：《实验力学》1997年第2期235-240,共6页Journal of Experimental Mechanics

摘　　要：本文简述了ＮＦ－３风洞二元实验段侧壁边界层吹除控制系统及具有吹气的模型实验方法，给出了不同吹气系数对风洞边界层的控制效果以及对相对厚度为７％的单段翼型实验结果的影响。初步实验研究结果表明，该控制系统能有效地改善风洞侧壁边界层的流动状态，减小侧壁干扰。The tangentially blowing sidewall boundary layer control system for a 2 D test section of NF 3 wind tunnel and the relevant model experiment method are presented briefly in this paper. The effects of different blowing coefficients on the efficiency of sidewall boundary layer control and on the experiment results for an airfoil with relative thickness 7% are given. This work shows that the control system will improve the sidewall boundary layer flow and give an improved 2 D flow characteristics of the test section.

关 键 词：二元风洞 翼型 侧壁干扰 吹气控制系统 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] V211.71