攻角对双三角翼旋涡特性影响的数值模拟  

Numerical Simulation of Effect of Attack Angle on the Vertex Characteristics of Double-Delta Wing

作　　者：杨小亮[1] 刘伟[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2008年第5期1-5,共5页Journal of National University of Defense Technology

基　　金：国家重大基础研究资助项目(61351);国家自然科学基金资助项目(90716015)

摘　　要：采用数值方法研究了双三角翼上涡流运动随攻角的变化规律。计算取层流假设，研究了攻角在5°-30°，76°／40°后掠双三角翼绕流的流场结构随攻角的变化，并对双三角翼上涡破裂现象对流场结构及气动力性能的影响进行了分析。结果表明，双三角翼上的多涡结构存在强烈的相互影响，较大的攻角会导致涡破裂在翼面上发生，严重影响了双三角翼的气动力性能。Numerical investigation of the vertex flow characteristics on double-delta wing was presented. The flows over the 76/40- deg double-delta wing were computed with complete laminar when attack angles varies from 5-deg to 30-deg. The flow structures were exhibited in different angles and the analysis of the aero-dynamic characteristics was presented. The investigation shows that vortexes on the double-delta wing surface may fiercely interact with each other and the burst of vortexes caused by large attack angle will exert great influence on the aero-dynamic characteristics of double-delta wing.

关 键 词：双三角翼 涡破裂 分离流 数值模拟 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]