低速风洞旋转流场下滚转振荡动导数试验技术研究  

Investigation of roll oscillation dynamical stability derivative in rotation flow field

作　　者：杜希奇[1] 卜忱[1] 于彦泽[1] 郑鑫杰[1] 王学俭[1] 

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《实验流体力学》2005年第4期46-48,55,共4页Journal of Experiments in Fluid Mechanics

摘　　要：介绍了中国航空工业空气动力研究院自主开发的旋转流场下单自由度振荡系统及相应的试验技术。尾旋特性分析及预测时所使用的动导数通常是在常规流场中获得的,测得的动导数没有体现旋转流场的影响。该项试验技术通过在旋转流场中进行强迫振荡运动来获取飞机尾旋过程中的动稳定性导数,实现了对流动的真实模拟。在FL-8风洞中采用某型号飞机的动导模型进行了旋转流场下滚转振荡试验研究,对试验数据进行简单分析。分析结果表明:该系统试验性能稳定,试验数据可靠,可以有效的应用于现代飞机的振荡尾旋和飘叶式尾旋过程的气动力特性研究和预测。A technology of wind tunnel test developed by CARIA for acquiring dynamical stability derivative in rotation flow field is described in this paper. The dynamic stability derivatives which are used for analysis and prediction the characters of spin are acquired in routine flow field usually, which has no effect of rotation. The technology acquires the dynamic stability derivate of the combined motion generated by superpositioning body-axis forced oscillation over a steady velocity vector rotation, which can simulate the flow field accurately. An aircraft model was tested in the FL-8 low speed wind tunnel. The test data were analyzed. The results show that the performance of the test system is stable and the test data gained are credible. The technology can be effectively applied to researching and predicting the aerodynamic characteristics of modem aircraft＇ s oscillatory spin or falling leaf motion.

关 键 词：尾旋 单自由度振荡 风洞试验 旋转流场 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]