80°/65°双三角翼模型大迎角气动特性风洞实验研究
Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing
-
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.Abstract: The aerodynamic characteristics,pressure distribution and flowfield evolution of an 80°/65° double-delta wing model have been studied in φ3.2m low speed wind tunnel at CARDC by means of force measurement,pressure measurement and PIV technique.The Reynolds number is 0.49~1.3( × 106)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 suctionpeak disappears gradually and pressure coefficient decreases evidently.After 40° AoA,the suction peak disappears completely and leading edge vortex breaks down totally.
下载:
