可变形飞行器机翼两种变后掠方式及其气动特性机理  

Morphing aircraft wing variable-sweep:two practical methods and their aerodynamic characteristics

作　　者：陈钱[1] 白鹏[1] 李锋[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《空气动力学学报》2012年第5期658-663,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金重点项目(90816026)

摘　　要：为了探索可变形飞行器机翼以不同方式变后掠时的气动特性差异及其物理机理,对旋转变后掠和剪切变后掠翼身组合体进行了宽广速域的绕流流场数值模拟,并对其气动特性与机理进行了分析。计算中,采用粘性可压缩流动的数值模拟方法和三棱柱-四面体的非结构-结构混合网格。结果表明:剪切变后掠具有优于旋转变后掠的特性,前者在宽广的速域内均具有显著优越的升阻比和阻力,主要原因在于不同变后掠方式所引起的流场结构的显著差异。In order to explore the methods of morphing aircraft variable-sweep and their aerodynamic characteristics, numerical simulation of the flow fields of a rotating variable-sweep wing-body and a shearing variable-sweep wing-body was conducted, and the aerodynamic characteris lyzed. Numerical simulation method of viscous compressible flow and hybr used. The results demonstrate that： shearing variable-sweep has better cha sweep in that the former has better lift-to-drag ratio and drag when flying 0.3 to M∞0.8, and the main reason is distinct flow field structure cause methods. tics and its mechanism were ana- id grid of prism-hexahedron were racteristics than rotating variable- at a speed in the range from M∞ d by the different variable-sweep

关 键 词：变形飞机 变后掠 旋转变后掠 剪切变后掠 气动效率 诱导阻力 

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]