实验流体力学2011，Vol.25Issue(3)：50-55,6.
Φ3.2m风洞战斗机大迎角试验关键技术研究
Key technique for high angle of attack test of fighter aircraft in φ3.2m low speed wind tunnel
孙海生 1祝明红 2黄勇 2刘志涛2
作者信息
- 1. 西北工业大学,西安710072
- 2. 中国空气动力研究与发展中心,四川绵阳621000
- 折叠
摘要
Abstract
The key test technique for aerodynamics of fighter at high angle of attack in φ3.2m low speed wind tunnel has been introduced, including model attitude correction technique at the condition of oscillation, stall flutter restrainability technique for wind tunnel models supported by wire sting, real time measurement technique of wind speed and so on. A continuous sweep test technique has been developed and successfully applied in the force measurement test of a fighter model at high angle of attack. The test results indicated that these key test technique could meet the needs of wind tunnel test for advanced fighter at high angle of attack.关键词
战斗机/大迎角/模型姿态角测量/振动/实时速压测量/连续扫描Key words
fighter aircraft/ high angle of attack/ model attitude measurement/ stall flutter/ real time wind speed measurement/ continuous sweep分类
航空航天引用本文复制引用
孙海生,祝明红,黄勇,刘志涛..Φ3.2m风洞战斗机大迎角试验关键技术研究[J].实验流体力学,2011,25(3):50-55,6.
