摘要
提出一种上下错开的无尾联接翼,即前翼或者后翼上反一定角度,使得前后翼垂直方向的相对距离从翼根处开始到翼梢处逐渐增大,以达到减小前后翼气动干扰的目的,搭接的小翼具有翼梢小翼作用,可有效减小诱导阻力。采用基于RANS方程的数值方法,研究了前后翼分别上反10°,20°和30°时对总体气动特性的影响,结果表明,当前翼上反且上反角为30°时其联接翼系统气动性能最佳。对该联接翼布局在Ma=0.85,0.95和1.20下进行了数值分析,结果表明,其升力系数变化较小,阻力系数在Ma>0.85后才急剧增大,有应用于未来跨声速/超声速客机布局的潜力。
A new joined wing configuration was presented, that is the front/rear wing has certain dihedral angle. The vertical distance between front and rear wings was gradually increased. The connection part has similar function to winglet, and the aerodynamic interference effect between wings could be reduced. RANS based simulations were made to investigate aerodynamic effect of different dihedral angles （ 10°, 20°, and 30°）. Results show that 30°dihedral angle of front wing could lead to maximum aerodynamic efficiency. Numerical simulations with different Mach number （0. 85, 0. 95, and 1.20） were also pres- ented. The lift coefficient is approximately constant and the drag coefficient will not rapidly increase until Mach number is bigger than 0. 85, indicating that it has the potential for being used in the future transon- ic/supersonic civil transport aircraft.
出处
《飞行力学》
CSCD
北大核心
2017年第3期28-31,36,共5页
Flight Dynamics
基金
航空科学基金资助(2014ZA55001
2016ZA55001)
河南省高等学校重点科研项目资助(15A590002)
郑州航空工业管理学院青年骨干教师资助计划(2015-21)
关键词
无尾布局
联接翼
气动特性
数值模拟
tailless configuration
joined wing
aerodynamic performance
numerical simulation
