翼身融合布局中央机体翼型设计研究  

Center Body Airfoil Design for Blended Wing Body Configuration

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

机构地区：[1]西北工业大学无人机研究所,陕西西安710065 [2]西北工业大学航空学院,陕西西安710072

出　　处：《西北工业大学学报》2018年第2期203-210,共8页Journal of Northwestern Polytechnical University

摘　　要：针对翼身融合布局中央机体翼型设计,在满足总体装载约束条件下,研究对称翼型、后卸载翼型、前加载翼型和前加载-后卸载翼型的气动影响规律。150座级BWB布局研究结果表明,采用对称翼型时,外翼需采用较大的负几何扭转角以实现静稳定设计状态下的正零升力矩,但升阻性能损失较大;采用前加载翼型时,受布局平面形状限制,不易达到正零升力矩;采用后卸载翼型或前加载-后卸载翼型时,合理设计前加载或后卸载的区域及大小,可获得升阻及力矩特性较为理想的气动设计结果。翼身融合飞翼布局无人机应用研究表明,采用具有前加载特征的"鹰勾"隐身前缘设计,气动性能损失小。To design the center-body airfoil of a blended wing body configuration,the aerodynamic effects of the symmetrical airfoil,trailing-edge reflexed airfoil,leading-edge loaded airfoil and leading-edge loaded plus trailing-edge reflexed airfoil are investigated based on the constraints of system arrangement.A 150-passenger BWB configuration is studied;for a center-body with symmetrical airfoil,the larger outer-wing geometrical twist should be used to fulfill the positive zero-lift pitching moment according to the design requirements of longitudinal static stability,however,lift to drag ratio shows a big decrease.For leading-edge loaded airfoil,it is difficult to achieve a positive zero-lift pitching moment because of the platform limitation.For trailing-edge reflexed airfoil or leading-edge loaded plus trailing-edge reflexed airfoil,it is easy to achieve ideal design results when reasonably designing the leading-edge loading and trailing-edge unloading.The application of a blended wing body UAV shows that the loss of aerodynamic characteristics is small when adopting the"eagle hook"stealth leading edge that has the characteristics of leading edge loading.

关 键 词：翼身融合布局 翼型 CFD 民机 无人机 

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]