一种高升阻比非常规翼身融合燕尾气动布局

A high lift-to-drag ratio unconventional blended-wing-body aerodynamic configuration with swallow tail

未来高性能先进飞行器研发不仅对升阻比、最大升力系数等气动性能大幅提升提出了迫切需求,还面临更为严苛的总体/结构/隐身/飞控等各专业设计约束和要求。从飞行器平台总体顶层设计角度和工程应用背景出发,基于大有效容积隐身机身和高升力大展弦比隐身自然层流机翼,结合同时对机身/机翼、后体/燕尾进行几何和气动高效一体化融合等设计思想,开展了一种高升阻比非常规翼身融合燕尾气动布局设计优化与性能测试研究。CFD计算和风洞试验结果表明设计方案在马赫数0.194、雷诺数5.2×105工况下最大升阻比约31.2,气动性能较为优异,同时基本纵向/横航向气动特性以及燕尾舵效等可满足飞控需求;红外转捩测量试验结果显示其自由转捩位置与层流翼型/机翼气动计算结果符合较好;表面流动分离丝线试验结果显示燕尾受到机翼下洗影响较为显著,后续可进一步开展深入研究。

The future development of advanced high-performance aircraft not only raises an urgent demand for significant improvement in aerodynamic performance such as the lift-to-drag ratio and maximum lift coefficient,but also faces more stringent design constraints and requirements of various disciplines such as overall/structural/stealth/flight control.According to the overall top-level aircraft design and engineering applications,we conduct an unconventional blendedwing-body swallow tail aerodynamic layout design optimization and performance analysis based on the new blendedwing-body integration design idea of large effective volume stealth fuselage,high lift and large aspect ratio stealth natural laminar flow wing,and efficient simultaneous geometric and aerodynamic integration design of fuselage/wing,and rear body/swallow tail.The results of CFD calculation and the wind tunnel test show that at Mach number Ma=0.194,Reynolds number Re=5.2 ×105,the maximum lift-to-drag ratio is about 31.2,and the aerodynamic performance is excellent.Meanwhile,the basic longitudinal/transverse aerodynamic characteristics and swallow tail rudder effect can meet the flight control requirements.The transition infrared measurement test results show that the free transition position is in good agreement with the laminar airfoil/wing aerodynamic design theory.The surface flow separation wire test results show that the swallow tail is significantly affected by the wing downwash flow,with further research to be conducted in the future.