三角翼破裂涡流的非定常特性  

Unsteady Characteristics of Vortex Breakdown over Delta Wing

作　　者：张明禄[1] 杨翊仁[1] 吕志咏[2] 

机构地区：[1]西南交通大学力学与工程学院,四川成都610031 [2]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《西南交通大学学报》2012年第5期832-835,共4页Journal of Southwest Jiaotong University

基　　金：国家自然科学基金资助项目(10272014;11102172);航空科学基金资助项目(01A51041);中央高校基本科研业务费专项资金资助项目(SWJTU11CX071)

摘　　要：为了研究飞机的三角翼前缘涡破裂后,破裂涡流的非定常特性,在风洞中进行了75°后掠三角翼的动态测压实验.实验结果表明:三角翼翼面的压力脉动强度变化和翼面上前缘涡的流态是正相关的,在前缘涡破裂迎角区,上翼面的压力脉动强度最高达到33 Pa,抖振强度随迎角的变化趋势与上翼面的压力脉动随迎角的变化趋势相同.通过对压力信号的分析得出,三角翼翼面上的压力脉动主要是由破裂涡流中的螺旋波引起的,螺旋波产生了三角翼机翼抖振.In order to investigate the unsteady characteristics of the broken vortices over delta wing after the leading edge vortices were broken down,experiments of dynamic pressure measurement were carried out on the surface of the 75° sweep delta wing in a wind tunnel.Experimental results show that the root mean square（RMS） pressure fluctuation is positively correlated with the fluid state of leading edge vortices on the top surface of delta wing.At the angle of attack region with leading edge vortices breakdown,the maximal RMS pressure fluctuation is 33 Pa.With increasing angle of attack,the variation of buffeting strength has the same tendency as that of RMS pressure fluctuation.Analysis of the pressure signal shows that the pressure fluctuations over the delta wing are mainly caused by the spiral wave of the broken-down vortex flow,which leads to the buffeting of the delta wing.

关 键 词：三角翼 前缘涡 涡破裂 螺旋波 抖振 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]