大攻角风洞自由飞动导数实验研究  

EXPERIMENTAL INVESTIGATION OF DYNAMIC STABILITY DERIVATIVES AT HIGH ANGLES OF ATTACK IN WIND TUNNEL FREE-FLIGHT

作　　者：许可法[1] 何龙德[1] 李明娟 程淑华[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《航空学报》1993年第8期B394-B397,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：实验是在0.2×0.2m^2超音速风洞中进行的,其来流Mach数为2.0。模型为带翼导弹模型。实验时用气体发射装置将模型向实验段上游发射;并以另一气流横吹模型使其呈大攻角状态飞行。最大攻角可达100°。采用高速鼓轮相机记录模型飞行姿态随时间的变化。用改进的数值积分法进行数据处理,求得俯仰阻尼导数随攻角的变化。This paper describes a wind tunnel free-flight technique for measuring pitch-damping derivatives of a missile model at high angles of attack. The tests were performed in a 20cm by 20cm supersonic wind tunnel with free-stream Mach number of 2.0. Test model is a basic finned configuration. The model was released by a pneumatic launcher. The maximum angle of attack of 100 degrees can be achieved in free-flight testing. Model trajectories were recorded by a high-speed drum camera. Pitch-damping moment derivatives versus angles of attack were obtained by numerical integral method.

关 键 词：风洞自由飞 大攻角 数据处理 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]