翼身融合布局低速风洞试验研究  

Low Speed Wind Tunnel Test of a Blended Wing Body Configuration

作　　者：李沛峰 张彬乾[2] 陶于金[1] 李栋[2] Li Peifeng;Zhang Binqian;Tao Yujin;Li Dong(365th Institute,Northwestern Polytechnical University,Xi’an 710065,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学第365研究所,西安710065 [2]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2019年第1期29-35,共7页Advances in Aeronautical Science and Engineering

摘　　要：翼身融合布局(BWB)综合性能突出,是未来民用航空领域飞行器发展的必然趋势,研究BWB布局的气动特点及流动机理,对开展BWB布局设计具有重要的支撑作用。采用测力、丝线流动显示的风洞试验方法并辅以CFD方法,开展300座级BWB布局(BWB-1)低速气动特性、流动机理及通气发动机短舱影响研究。结果表明:与Early BWB、N2A布局相比,BWB-1具有更好的低速纵向气动性能,具有横向静稳定、航向静不稳定量值较小,航向增稳与控制难度较小等优点;揭示了布局的流动发展过程及具有和缓失速特性的物理原因;通气发动机短舱对提高最大升力及增加航向静稳定性有利,对横向静稳定性影响较小,但使得阻力和低头力矩增加;CFD纵向计算结果与试验基本一致,验证了CFD方法的有效性。Blended wing body(BWB) configuration will be the inevitable trend of the aircraft using in the future civil aviation for its excellent performance. Aerodynamic and flow mechanism investigations of the BWB configuration will provide important support for its design. Wind tunnel tests include force measurements and tuft visualization, in addition to computation fluid dynamics(CFD) simulation, are used to investigate the low speed aerodynamic characteristics and flow mechanism and effects of flow-through nacelles for a 300-passenger BWB configuration(BWB-1). Test results show that longitudinal aerodynamic characteristics of BWB-1 are better than those of the Early BWB or N2A. BWB-1 possesses lateral static stability and directional static instability, however, low value of the directional instability degrades the difficulty in directional stability augmentation and control. Investigation also reveals flow development and physical mechanism of a mild stall characteristic of the configuration. Flow-through nacelles are beneficial to both maximum lift and directional stability, and have minimal effects on lateral stability;however, drag and pitch-down moment are increased. Results from CFD simulation show good agreement with tunnel test data, which demonstrate the validation of the CFD method.

关 键 词：翼身融合布局 风洞试验 流动机理 发动机短舱 计算流体力学 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]