80°/65°双三角翼模型大迎角气动特性风洞实验研究(英文)  

Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing

作　　者：孙海生[1] 姜裕标[2] 刘志涛[2] 史喆羽[2] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国空气动力研究与发展中心低速所,四川绵阳621000

出　　处：《实验流体力学》2011年第6期6-12,共7页Journal of Experiments in Fluid Mechanics

摘　　要：在气动中心低速所Φ3.2m风洞综合运用测力、测压、烟流和PIV流场测量等手段对80°/65°双三角翼模型大迎角气动特性、压力分布及空间流场结构演化规律进行了研究。试验雷诺数为0.49～1.3(×106),迎角为0°～60°。研究结果表明:不同实验手段获得的研究结果之间具有较好的相关性,该双三角翼在迎角30°时升力系数出现最大值,在迎角30°～37°之间,升力系数变化不大,之后升力系数急剧下降;迎角超过30°,前缘涡出现破裂,迎角由38°增至40°,吸力峰消失,压力系数骤降,迎角超过40°吸力峰完全消失,前缘涡完全破裂。The aerodynamic characteristics, pressure distribution and flowfield evolution of an 80°/65° double-delta wing model have been studied in Ф3.2m low speed wind tunnel at CARDC by means of force measurement, pressure measurement and PIV technique. The Reynolds number is 0.49-1.3（×10^6）and the range of angle of attack（AoA） is between 0° and 60°. The study indicates that the results obtained from different types of tests have good correlation. The lift coefficient reaches maximum at 30° AoA, changes slightly between 30°-37° AoA, then drops rapidly as AoA increases. When AoA exceeds 30°, the leading edge vortex begins to break down. From 38° to 40° AoA, the suction ,peak disappears gradually and pressure coefficient decreases evident ly. After 40° AoA, the suction peak disappears completely and leading edge vortex breaks down totally.

关 键 词：双三角翼 大迎角空气动力学 流动机理 风洞实验 涡破裂 

分 类 号：O35[理学—流体力学] TJ530[理学—力学]