翼身融合布局平面参数对变弯度减阻特性分析  

Drag reduction characteristics analysis of variable camber based on plane parameters of blended wing body configuration

作　　者：王雨桐 刘悦 王浩 杨体浩 刘红阳[1] 周铸[1] WANG Yutong;LIU Yue;WANG Hao;YANG Tihao;LIU Hongyang;ZHOU Zhu(Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000 [2]西北工业大学航空学院,西安710072

出　　处：《北京航空航天大学学报》2025年第2期525-545,共21页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：变弯度技术能提升飞行器气动性能,与翼身融合(BWB)布局相结合可进一步增强其气动优势。但无尾BWB仅靠后缘舵面配平,纵向力臂短,配平阻力惩罚大,因此进行BWB后缘变弯度设计时需充分考虑配平阻力损失。针对无尾BWB,考虑平面参数对后缘舵面配平能力的影响,基于全局优化方法研究了不同机翼后掠角和机翼位置的BWB构型上后缘变弯度技术的减阻原理和作用效果。结果表明:在不同升力系数下,配平阻力损失都显著减小变弯度技术的减阻收益。BWB平面参数通过影响激波强度与配平能力,左右变弯度技术的减阻收益并影响舵面偏转角度。相比于基准构型,增大后掠角会使得小升力系数下减阻收益增加、大升力系数下降低;而机翼位置靠前,则会使得不考虑力矩配平时减阻收益增加、考虑力矩配平时阻收益降低。工程上进行无尾飞行器后缘变弯度设计时,应综合考虑后缘变弯度的减阻收益以及变形所需的舵面偏转角度。The variable camber technology can adaptively improve the aerodynamic performance of the aircraft,so combining it with the blended wing body(BWB)configuration can further exert its aerodynamic advantages.However,the tailless BWB only uses the trailing edge flap surface for trimming,with a shorter longitudinal moment arm,resulting in a large penalty in trim drag.Therefore,the trimming of drag loss should be fully considered in the design of the variable camber at the trailing edge of BWB.Since the plane parameters would affect the trimming capability of each flap surface at the trailing edge of tailless BWB,this paper adopted the global optimization method to study the drag reduction principle and effects of the variable camber technology at the trailing edge of BWB with different sweepback angles and different wing positions.The results show that,under different lift coefficients,the trim drag loss significantly reduces the drag reduction benefits of the camber variation technology.Secondly,the planar parameters of BWB affect the shock wave intensity and trim ability,thus influencing the drag reduction benefits of the camber variation technology and the deflection angles of the control surfaces.Compared with the baseline configuration,increasing the sweep angle can increase the drag reduction benefits at small lift coefficients and decrease them at large lift coefficients.When the wing position is forward,the drag reduction benefits increase when moment trimming is not considered,but decrease when moment trimming is considered.When designing the variable camber at the trailing edge of the tailless aircraft in engineering,it is necessary to comprehensively consider the drag reduction benefits of the variable camber at the trailing edge and the deflection angle of the flap surface required for deformation.

关 键 词：翼身融合布局 变弯度机翼 减阻 配平特性 优化设计 

分 类 号：V221.41[航空宇航科学与技术—飞行器设计]