分布式螺旋桨倾转角度对机翼气动性能的影响  

Influence of distributed propeller tilt angle on aerodynamic performance of wing

作　　者：廖逸枭 郑敏 章录兴 余发源 段焰辉 LIAO Yixiao;ZHENG Min;ZHANG Luxing;YU Fayuan;DUAN Yanhui(School of Aeronautics and Astronautics,Sun Yat-sen University,Shenzhen 518107,China;School of Systems Science and Engineering,Sun Yat-sen University,Guangzhou 510275,China)

机构地区：[1]中山大学航空航天学院,广东深圳518107 [2]中山大学系统科学与工程学院,广东广州510275

出　　处：《中山大学学报（自然科学版）（中英文）》2023年第5期115-127,共13页Acta Scientiarum Naturalium Universitatis Sunyatseni

基　　金：广东省基础与应用基础研究基金(2023A1515010036)。

摘　　要：分布式电推进飞行器通过机翼前缘规律分布的螺旋桨滑流作用改善飞行器的升阻特性。本文采用类X-57的分布式电推进机翼构型,通过等效盘方法研究了分布式螺旋桨倾转对机翼气动特性的影响。介绍了等效盘方法,并用实验数据和CFD计算数据对其进行验证。对比了在不同来流迎角下起降构型在有无滑流影响下的升阻力特性。分别对机翼起降构型分析了螺旋桨倾转角度对机翼气动性能的影响。结果表明,螺旋桨倾转改变了滑流对机翼的实际迎角和推力方向,当实际迎角减小时,机翼的气动升力系数也随之减小,但是倾转导致的螺旋桨推力在升力方向上的分量提高了机翼的有效升力系数;在5.5°迎角下,对于起飞构型,螺旋桨倾转角为20.18°时获得最大有效升力系数,约为2.445 1,对于降落构型,螺旋桨倾转角为23.83°获得最大有效升力系数,约为3.628 8。Distributed electric propulsion aircraft improve the lift-drag characteristics of the aircraft by using propellers distributed along the leading edge of the wing to generate slipstream.In this paper,we use a wing configuration similar to the X-57 and study the effect of propeller tilt on the wing aerodynamics using an actuator disk method.We introduce the actuator disk method and validate it with experimental data and CFD calculation data.We compare the lift-drag characteristics of the take-off and landing configurations with and without slipstream for different angles of attack.The effect of the propeller tilt angle on the aerodynamic performance of the wing is analyzed respectively for the take-off and landing configurations of the wing.The results show that propeller tilt changes the effective angle of attack and thrust direction of the slipstream on the wing.When the effective angle of attack decreases,the aerodynamic lift coefficient of the wing also decreases,but the component of propeller thrust in the lift direction due to tilt increases the effective lift coefficient of the wing.At 5.5° angle of attack,for the take-off configuration,the maximum effective lift coefficient is obtained when the propeller tilt angle is 20.18°,which is about 2.445 1,and for the landing configuration,the maximum effective lift coefficient is obtained when the propeller tilt angle is 23.83°,which is about 3.628 8.

关 键 词：分布式电推进 等效盘 螺旋桨倾转 有效升力系数 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]