摘要
以先进战斗机的非常规机动为对象,发展了一种适用于大幅度运动变化的非结构嵌套网格生成方法,建立了一整套非定常流场N-S方程数值求解方法。在对三角翼动态气动特性计算验证的基础上,模拟了飞机过失速机动条件下飞行姿态和来流速度的变化特征,对鸭式布局战斗机"眼镜蛇机动"的非定常涡结构、非定常气动力效应和气动特性进行了数值研究,揭示了鸭式布局战斗机"眼镜蛇机动"的非定常流场机理。
An unstructured overset grid generation method is presented to study large amplitude movements of unconventional maneuver of an advanced fighter and a numerical method is developed based on the Navier-Stokes（N-S） equations for analyzing unsteady flow problems.Based on calculation and validation of the dynamic characteristics of a delta wing,flight attitude and velocity variation are simulated when the aircraft is under the condition of post-stall maneuvers.The numerical investigation of the unsteady vortex structure,the unsteady aerodynamics and the aerodynamic characteristics reveal the unsteady flow mechanism of the canard aircraft through Cobra maneuver.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2014年第6期874-881,共8页
Journal of Nanjing University of Aeronautics & Astronautics
基金
江苏高校优势学科建设工程基金资助项目
关键词
嵌套网格
非常规机动
非定常流场
鸭式布局
overset grids
unconventional maneuver
unsteady flow
canard layout
