3种不同机翼构型的地效翼气动特性优化实验研究  

An Experiment with Optimization of Aerodynamic Characteristics about Ground Effect Wings Based on Three Different Wing Configurations

作　　者：邓博闻 代钦[1,2] DENG Bowen;DAI Qin(School of Mechanics and Engineering Sciences,Shanghai University,Shanghai 200072,China;Shanghai Institute of Applied Mathematics and Mechanics,Shanghai 200072,China)

机构地区：[1]上海大学力学与工程科学学院,上海200072 [2]上海市应用数学和力学研究所,上海200072

出　　处：《空军工程大学学报》2024年第5期60-68,共9页Journal of Air Force Engineering University

基　　金：国家自然科学基金(11472169)。

摘　　要：机翼的几何构型是影响地效飞行器空气动力学特性的重要参数,为改善地效飞行器升力、阻力特性,采用拖曳水槽实验测量了下反前掠翼和具有仿生凹凸前缘下反前掠翼的升力、阻力特性和尾流速度场,并在分析翼尖涡流场结构的基础上从展向流动的角度讨论了机翼升力阻力变化的机理。结果表明,在地效区内,下反前掠结构可以有效改善机翼绕流特性,抑制翼尖涡的形成和发展、增大了涡心距,起到增升减阻的效果,并且机翼越靠近地面,增升减阻的效果越明显。在此基础上,凹凸前缘可以进一步优化机翼绕流特性,降低翼尖涡强度,使诱导阻力减小。在小间隙比、小攻角工况中,带凹凸前缘的下反前掠结构的仿生翼具备最优的航行经济性。上述研究可为改善地效翼的飞行性能并促进地效翼设计理论的发展提供参考。In order to improve lift and drag characteristics of ground effect aircraft, experiments are made by measuring lift, drag characteristics, and wake velocity fields with a downward-forward swept wing and a biomimetic wing. On the basis of analyzing the wing tip vortex flow field structure, the mechanism of wing lift and drag changes is discussed from the perspective of spanwise flow. The results show that within the ground effect zone, the downward-forward structure can effectively improve the flow characteristics of the wing, suppress the formation and development of wing tip vortex flow, increase the vortex center distance, the effect is made with the lift being increasing and drag force being decreasing, and the closer the wing is to the ground, the more obvious the effect is. On this basis, the concave convex leading edge can further optimize the flow characteristics of the wing, reduce the intensity of the wing tip vortex, and reduce the induced drag. In small clearance ratio and small angle of attack conditions, the biomimetic wing with a downward-forward sweep structure with a concave convex leading edge has the optimal navigation economy. This provides a reference for improving the flight performance of ground effect wings and promoting the development of ground effect wing design theory.

关 键 词：地面效应 平直翼 下反前掠翼 仿生翼 升力和阻力 PIV实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] O355[理学—流体力学]