摘要
碟形升力体飞行器采用了翼身融合的小展弦比气动布局.利用重心前移方式解决了横向稳定性问题,其效果在模型试飞实验中得到了验证.由于展弦比小而导致诱导阻力较大,为减小诱导阻力,在风洞中对一种后掠鱼鳍形小翼进行了吹风试验.模型安装翼尖小翼后,风洞测量其最大升阻比在30m/s风速下提高了70%.在试飞模型中验证了这种小翼不仅可以增大载重量而且增强了横向稳定性.为进一步了解碟形升力体飞行器的气动特性,利用数值方法对升力体流场进行了模拟研究.数值结果显示,由于展弦比小,升力体翼尖处诱导旋涡对升力体的气动特性影响较大.
Saucer-shaped aircraft is a new type aircraft configuration with blended fuselage and wing. Through the method of changing centre of gravity, flight stability was acquired and validated in the flight test. A type of fin-shaped wing-tip winglet applied to this aircraft to reduce induced drag was presented. Compared to the original type without winglet, the lift to drag ratio of new model can be improved by 70% at the speed of 30 m/s in wind tunnel. The results of tunnel experiments were verified successful in test flights. Not only its load was increased but also its aerodynamic performance was good. In order to realize its aerodynamical characteristics, computational investigation was performed to the flow field. By analyzing the results, wingtip vortex had important influence to its performance.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2010年第2期198-201,共4页
Journal of Beijing University of Aeronautics and Astronautics
关键词
机翼
机身
阻力系数
减阻
wings
fuselages
drag coefficient
drag reduction
