| 引用本文: | 汪超,周超英,谢鹏,张锐.翼型厚度和弯度对前飞扑翼气动性能的影响[J].哈尔滨工业大学学报,2018,50(4):28.DOI:10.11918/j.issn.0367-6234.201612156 |
| WANG Chao,ZHOU Chaoying,XIE Peng,ZHANG Rui.Effects of thickness and camber on aerodynamic performance of flapping wings during forward flight[J].Journal of Harbin Institute of Technology,2018,50(4):28.DOI:10.11918/j.issn.0367-6234.201612156 |
|
| 摘要: |
| 扑翼飞行器是一种模仿鸟类和昆虫飞行方式的新型飞行器.翼型参数设计对提高扑翼飞行器性能至关重要，为研究扑翼翼型厚度和翼型弯度对前飞扑翼气动性能的影响，基于自然界中飞行生物的实验观测结果建立了前飞扑翼气动特性计算模型，针对不同厚度和弯度的NACA系列标准翼型，采用计算流体力学方法求解二维不可压缩非定常Navier-Stokes方程，基于有限体积法并结合动态网格技术，分析了低雷诺数条件下对应不同来流速度的刚性前飞扑翼气动力、能耗、气动效率以及周围流场结构随翼型厚度和弯度的变化规律.结果表明，不同来流速度条件下扑翼推力和能耗均随翼型厚度的增大而逐渐减小，随着翼型厚度的增大，扑翼推进效率最大降幅达15.9%；翼型厚度的增加，降低了前缘涡强度并延迟了前缘涡的脱落.翼型弯度可以改变翼型的有效气动攻角，翼型弯度的增加可以显著提高翼型升力和升举效率，并促使尾流中心线向右下方倾斜；正向弯度扑翼在下扑行程能产生更大的升力，而负向弯度扑翼则在上挥行程中产生了更大的推力.
|
| 关键词: 翼型厚度 翼型弯度 扑翼 前飞 气动性能 |
| DOI：10.11918/j.issn.0367-6234.201612156 |
| 分类号:V211.3 |
| 文献标识码:A |
| 基金项目:国家自然科学基金联合基金(U1613227);深圳市创新环境建设计划重点实验室提升项目(ZDSYS20140508161547829) |
|
| Effects of thickness and camber on aerodynamic performance of flapping wings during forward flight |
|
WANG Chao,ZHOU Chaoying,XIE Peng,ZHANG Rui
|
|
(Shenzhen Graduate School, Harbin Institute of Technology, Shenzhen 518055 Guangdong, China)
|
| Abstract: |
| Flapping-wing aerial vehicle is a new type of aerial vehicle that mimics the flight mode of birds and insects. The design of airfoil parameters is crucial for improving the performance of flapping wing aerial vehicle. A numerical investigation into the effects of thickness and camber on aerodynamic performance of flapping wings during the forward flight is carried out through the solution of the two-dimensional incompressible unsteady Navier-Stokes equations using the computational fluid dynamics methods. The aerodynamic computational model with varying NACA series standard airfoil thickness and camber is built based on the observation of flying creatures. The aerodynamic forces, energy consumption, flight efficiency and flow field structure of the rigid wings with different incoming flow velocities under low Reynolds number are systematically analyzed using the finite element method coupled with the dynamic mesh method. It is found that the thrust force and energy consumption of the rigid wing with low Reynolds number decrease with increasing wing thickness at different incoming flow velocities, and the decrease in propulsive efficiency can reach as much as 15.9%. The leading edge vortex (LEV) intensity is reduced and the LEV shedding is delayed with the increase of airfoil thickness. On the other hand, the wing camber can change the wing angle of attack effectively. The positive camber can significantly improve the lift force and lifting efficiency and tilt the centerline of the wake towards the bottom right. The flapping wing with positive camber can produce large lift force during the downstroke, while the wing with negative camber can produce large thrust force during the upstroke.
|
| Key words: wing thickness wing camber flapping wing forward flight aerodynamic performance |
