考虑螺旋桨滑流影响的双发涡桨飞机气动特性研究  

Aerodynamics Analysis of Twin-Turboprop Aircraft with Propeller Slipstream Effects Considered

作　　者：王伟[1] 段卓毅[1] 耿建中[1] 王斌[1] 丁兴志[1] 

机构地区：[1]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《西北工业大学学报》2017年第6期1105-1111,共7页Journal of Northwestern Polytechnical University

摘　　要：螺旋桨滑流与飞机其他部件之间存在着复杂的气动干扰,将对双发涡桨飞机的气动特性产生较为显著的影响。以双发涡桨飞机为研究对象,采用多重参考系滑移网格技术进行流场数值模拟,研究了不同拉力系数下螺旋桨滑流以及滑流区内尾翼法向位置对全机气动特性的影响。研究结果表明:螺旋桨滑流效应将增加全机升力和阻力,降低全机升阻比,并导致小迎角区域俯仰力矩不稳定;随着拉力系数的增加,全机最大升力系数可增加40%,阻力系数增加150%,升阻比可降低50%,小迎角俯仰力矩拐点可增加8°,静稳定裕度可降低30%;合理地下移尾翼法向位置,可有效地利用螺旋桨滑流的影响,改善其俯仰力矩特性。研究结果对双发涡桨飞机的总体气动设计具有一定的工程指导价值。Aerodynamic interaction of propeller slipstream with aircraft parts will lead to significant influence on the complete twin-turboprop aircraft. Taking the twin-turboprop aircraft for example, the effects on the complete aircraft due to propeller slipstream and the normalized translation of horizontal wing under different thrust coefficient are studied by numerical simulation based on multiple reference frames （MRF） techniques. The research results and their analysis show preliminarily that：due to the effects caused by slipstream of propellers, the lift and drag will increase correspondingly, while the lift-drag ratio will decrease and the pitching moment will become unstable at the small AOA; with the increasing of thrust coefficient, the lift coefficient will increase by 40%, the Cd will increase by 150%, the lift-drag ratio will decrease by 50%, the inflection point at small angle of attack will increase by 8 degrees and the pitching static margin will decrease by 30%;rationally moving the horizontal wing down will make use of the slipstream effects, which will improve the pitching moment characteristics. The investigation is believed to be of some reference value to the design of twin-turboprop aircraft.

关 键 词：滑流 涡桨飞机 气动特性 静稳定性 升阻比 非线性 

分 类 号：V217.4[航空宇航科学与技术—航空宇航推进理论与工程] V216.7