Effects of flexibility on aerodynamic performance of delta wings with different sweep angles

作     者：LIU Yang,ZUO LinXuan & WANG JinJun Institute of Fluid Mechanics,Beijing University of Aeronautics and Astronautics and Fluid Mechanics Key Laboratory,Ministry of Education,Beijing 100191,China 

作者机构：Institute of Fluid Mechanics Beijing University of Aeronautics and Astronautics Fluid Mechanics Key Laboratory Ministry of Education 

出 版 物：《Science China(Physics,Mechanics & Astronomy)》 (中国科学：物理学、力学、天文学（英文版）)

年 卷 期：2010年第53卷第5期

页      面：915-922页

核心收录：

学科分类：080704[工学-流体机械及工程] 080103[工学-流体力学] 08[工学] 0807[工学-动力工程及工程热物理] 0805[工学-材料科学与工程（可授工学、理学学位）] 0704[理学-天文学] 0801[工学-力学（可授工学、理学学位）] 

基　　金：supported by the National Natural Science Foundation of China (Grant Nos. 10425207 and 10832001) 

主　　题：delta wing wing flexibility aerodynamics sweep angle 

摘      要：Force measurement and surface oil flow visualization experiments were conducted in a wind tunnel to investigate the effects of flexibility on aerodynamic performance of delta wings with different sweep *** experimental results indicate that the maximum lift coefficient is increased and the stall angle is delayed as the sweep angle increases for both rigid and flexible *** is also found that the maximum lift coefficients of the flexible wings with a sweep angle from 35° to 50° are higher than those of the rigid *** increment of the maximum lift coefficient in particular achieves 32.9% compared with the case without lift enhancement for the 40° flexible delta ***,the surface oil flow visualization experiments show that the stall of the flexible wing of the moderate low sweep angle is accompanied by helical flow structure,while the vortex bursting appears on the corresponding rigid wing.