环翼机低速气动特性风洞实验研究  

The Aerodynamics Research of Ring Wing Configuration in Low Speed Wind Tunnel

作　　者：李蒙[1] 邓彦敏[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《飞机设计》2008年第6期1-4,17,共5页Aircraft Design

摘　　要：环翼机具有前、后翼,前翼后掠,后翼前掠,机翼在翼尖处连接,形成一个环状结构。为了解环翼的气动特性及环翼的几何参数对环翼机气动特性的影响,本文在低速风洞中对3种不同几何参数环翼飞机进行了纵向及横向测力实验,其中包括前、后翼几何参数改变对气动特性的影响。实验结果表明,与常规飞机相比,环翼机具有如下优点:诱导阻力小,失速特性好,操稳性能易于满足。实验得到的有价值结果,对环翼布局飞机的气动计算和合理设计具有重要意义。Ring wing aircraft has an unconventional configuration, which combines swept-aft front wing and swept-forward rear wing joined at wingtip. The wings form an annulus shape in both planform and in front view. The three ring wing configurations have been experimented in low-speed wind tunnel. The longitudinal and lateral-directional aerodynamic characteristics of ring wing aircraft are discussed. The test results appears that ring wing provides the following advantages over conventional aircraft： lower induced drag, better stall characteristics, the pitching and yawing characteristics is improved. The experiment results have important meanings to the aero-dynamic calculation and reasonable design of ring-wing aircraft.

关 键 词：环翼机 尾迹流 风洞 

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]