摘要
研究了带柔性后缘的可变弯度自适应机翼在自适应变弯度过程中的气动特性。自适应变弯度过程中的气动力计算采用了基于弹簧理论的非结构动网格技术,求解NS方程时采用有限体积的二阶迎风格式离散,时间推进为隐格式双时间推进方法。通过计算柔性后缘机翼的升力特性、阻力特性及升阻比特性,并与带刚性后缘机翼的气动特性进行比较,发现柔性后缘机翼在后缘偏转时,其最大升阻比对应的迎角随着偏转角增大而降低。在中等迎角及接近失速迎角情况下,柔性后缘机翼升力系数明显优于刚性后缘机翼,并且其升力线变化较为平缓,有效迎角范围更大。
The aerodynamic characteristics of a flexible trailing edge adaptive wing are solved, where the NS equations are discretized with second order upwind scheme and dual time unstructured deforming meshes. The lift, drag and lift-to-drag ratio characteristics are calculated and compared with those of rigid wing with the same airfoil . It is found that the lift increases with the increasing trailing edge deflection linearly within linear lift ranges. Lift-to-drag ratio decreases with the increasing deflection angle. The lift characteristics of the flexible trailing edge adaptive wing are better than the corresponding rigid wing at middle to stall angle of attack, with moderate lift slope, and it offers more effective angle of attack.
出处
《应用力学学报》
CAS
CSCD
北大核心
2009年第3期548-553,共6页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金(10672135)
关键词
自适应机翼
柔性后缘
气动特性
非结构动网格
Adaptive Wing, flexible trailing edge, aerodynamic characteristics, unstructured deforming mesh.
