航空学报 > 2024, Vol. 45 Issue (6): 629630-629630   doi: 10.7527/S1000-6893.2023.29630

飞行器新概念气动布局设计专栏

一种高升阻比非常规翼身融合燕尾气动布局

刘柳1, 向先宏1(), 张宇飞2, 陈海昕2, 魏闯3, 朱剑1, 杨普2   

  1. 1.海鹰航空通用装备有限责任公司,北京 100074
    2.清华大学 航天航空学院,北京 100084
    3.航空工业空气动力研究院 高速高雷诺数气动力航空科技重点实验室,沈阳 110034
  • 收稿日期:2023-09-21 修回日期:2023-09-28 接受日期:2023-11-27 出版日期:2024-03-25 发布日期:2023-12-13
  • 通讯作者: 向先宏 E-mail:2007xxhong@163.com
  • 基金资助:
    国家自然科学基金(12372288)

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

Liu LIU1, Xianhong XIANG1(), Yufei ZHANG2, Haixin CHEN2, Chuang WEI3, Jian ZHU1, Pu YANG2   

  1. 1.CASIC UAV Technology Research Institute,Beijing 100074,China
    2.School of Aerospace Engineering,Tsinghua University,Beijing 100084,China
    3.Aviation Key Laboratory of Science and Technology on High Speed and High Reynolds Number Aerodynamic Force Research,AVIC Aerodynamics Research Institute,Shenyang 110034,China
  • Received:2023-09-21 Revised:2023-09-28 Accepted:2023-11-27 Online:2024-03-25 Published:2023-12-13
  • Contact: Xianhong XIANG E-mail:2007xxhong@163.com
  • Supported by:
    National Natural Science Foundation of China(12372288)

摘要:

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。

关键词: 未来先进飞行器, 大展弦比, 高升力, 非常规翼身融合, 燕尾气动布局, 风洞试验

Abstract:

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 blended-wing-body swallow tail aerodynamic layout design optimization and performance analysis based on the new blended-wing-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.

Key words: future advanced aircraft, high aspect ratio, high lift, unconventional blended-wing-body, swallow tail aerodynamic layout, wind tunnel test

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