俯仰-滚摆耦合复杂流场试验研究  

Experimental investigation on unsteady flow field about a coupled pitching-rolling delta wing

作　　者：唐敏中 张伟 何宏丽 

机构地区：[1]中国航空空气动力研究所,黑龙江哈尔滨150001

出　　处：《空气动力学学报》2001年第1期47-55,共9页Acta Aerodynamica Sinica

摘　　要：给出 8 0°三角翼模型在低速风洞中实施俯仰 滚摆耦合大幅度振动的复杂流场测量结果 ,包括静态和动态、单自由度俯仰和滚摆、俯仰 滚摆耦合运动条件下的流动显示结果和强迫俯仰、自由滚摆条件下的滚转角时间历程测量结果。分析了耦合运动对前缘分离涡和气动特性的影响 ,以及不同相位角和不同频率对耦合气动特性的影响。结果表明 ,双自由度的耦合运动比单自由度运动具有更为明显的动态迟滞特性 ,进一步推迟分离涡的破碎 ,推迟开始滚摆的攻角αwr。The paper gives the measurements results of complex flow field about a delta wing coupled pitching and rolling oscillation at high amplitude in low speed wind tunnel . The results contain flow visualization in static and dynamic, pitching or rolling alone, coupled pitching and rolling test condition, and the measurement of free rolling angle history. The effects of coupled motion on the leading edge vortex and aerodynamic character of the wing were analyzed. The test results showed, that the coupled motion has more obvious dynamic histeresis than the one free degree motion .The wing rock under pitching motion will shift to higher angle of attack α wr and has higher rocking frequency.

关 键 词：俯仰-滚摆耦合运动 复杂流场 滚转角时间历程 战斗机 大攻角机动飞行 气动特征 

分 类 号：V271.41[航空宇航科学与技术—飞行器设计] V211.7