The wind tunnel test technique for model free to tumble dynamic derivatives has been developed to meet the urgent needs for dynamic derivative measurements of aerospace aircraft models in the range of angles of attack of 0°～360°and to meet the needs for mechanism study of limit cycle oscillation phenomena.
风洞模型自由翻滚动导数试验技术是为满足航空航天飞行器 0°～ 36 0°全迎角范围内的动导数测量及产生极限环振动现象研究之急需而研制的。
The wind tunnel test technique for dynamic stability derivatives of the model free to tumble at hypersonic speeds has been developed to meet the urgent needs for dynamic derivative measurements of aerospace vehicles at angles of attack of 0°～360° and for mechanism study of limit cycle oscillation phenomenon.
高超声速风洞模型自由翻滚动导数试验技术是为满足航空航天飞行器 0°～ 360°全攻角范围内的动导数测量及产生极限环振动现象的研究之急需而研制。