摘要
以亚声速飞翼布局无人飞行器X-47B为研究对象,选用NACA4415bis为基准翼型,采用三维数值仿真计算方法,设计襟翼并研究其在不同迎角、不同下放角度下升阻力特性及表面压力分布。构建网格并进行无关性验证与可行性分析,网格划分方法符合翼型及简单襟翼特点,可准确分析流动形态及增升机理。数值分析结果表明其增升能力较初始外形有显著提高,增升设计在迎角小于等于12°、下放角度为8°时可实现升力系数要求并实现最大增升效果,迎角过大时下放襟翼会导致飞行器提前发生失速现象,但仍可实现部分增升效果。该增升方案适用于大多数翼身融合布局飞行器。
In this paper,the subsonic Blended-Wing-Body(BWB)UAV X-47B is taken as the research object.The NACA 4415bis airfoil is chosen as the reference airfoil,and the three-dimensional digital simulation method is used to design flaps.The lift drag characteristics and surface pressure distribution of the flaps at different angles of attack and descent are studied.Firstly,the mesh is constructed to verify the irrelevance and feasibility.The mesh generation method conforms to the characteristics of airfoil and simple flaps,and can accurately analyze the flow pattern and lift mechanism.The results of numerical analysis show that the lift-up capability is signi ficantly improved compared with the initial shape.When the angle of attack is less than or equal to 12 degrees and the angle of descent is 8 degrees,lift coe fficient requirements and the maximum effect of rising can be achieved.When the angle of attack is too large,lowering the flaps will lead to stall of the aircraft in advance.However,some lift effect can still be reached.The rising scheme is appropriate for most BWB aircrafts.
作者
李俊林
和敬杰
张昕喆
李国举
刘志棋
LI Jun-lin;HE Jing-jie;ZHANG Xing-zhe;LI Guo-ju;LIU Zhi-qi(Department of Aeronautical Engineering,Zhengzhou University of Aeronautics,Zhengzhou Henan 450015;Guizhou Anda Aviation Forging Co.,Ltd.,Anshun Guizhou 561005)
出处
《长沙航空职业技术学院学报》
2020年第2期74-78,共5页
Journal of Changsha Aeronautical Vocational and Technical College
基金
2016年航空科学基金“基于经济性和舒适性的先进公务机多学科优化设计方法研究”(编号:2016ZA55001)
2019年河南省科技攻关计划“支线级物流无人机超窄体机舱货物高效装载关键技术研究”(编号:192102210056)阶段性研究成果。
关键词
简单襟翼
增升装置
翼身融合布局
气动特性
优化设计
simple flaps
lift-up device
Blended-Wing-Body
aerodynamic characteristics
optimal design
作者简介
李俊林(1999-),男,贵州安顺人,研究方向为飞行器设计与空气动力学;刘志棋(1969-),男,江西萍乡人,高级工程师,研究方向为航空材料。
