Volume 36, Number 2, April 2018
|203 - 210
|03 July 2018
Center Body Airfoil Design for Blended Wing Body Configuration
Institute of UAV, Northwestern Polytechnical University, Xi'an 710065, China
2 School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
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.
Key words: airfoils / wings / computational fluid dynamics / design / aerodynamic configurations / lift drag ratio / blended wing body / civil transport / unmanned aerial vehicles(UAV)
关键字 : 翼身融合布局 / 翼型 / CFD / 民机 / 无人机
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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