摘要
采用SSTk-ω二方程湍流模型,通过解耦求解雷诺平均N-S方程实现对巡飞器无舵偏情况下湍流流场的数值模拟。对巡飞器低雷诺数绕流流场进行了计算,分析了其在无舵偏情况下气动特性随迎角、侧滑角的变化情况。仿真结果表明,巡飞器采用充气式机翼后,具有很好的失速性能与较好的大迎角稳定性。
This thesis uses the SST k-ω two equations turbulence model, with the solution of the Renault average N-S equation, it simulates the turbulence flow field of the loitering aerial vehicle while it doesn＇t have the deflexion of the helms. With the calculation of the low Renault number circle flow field for the loitering aerial vehicle, the thesis analyzes that aerodynamic characteristics of the loitering aerial vehicle changes with the angle of attack- and the sideslip angle while it doesn＇ t have the deflexion of the helms. The result of the simulation indicates, the loitering aerial vehicle with inflatable wing has good stallout capability and excellent stability at high angles of attack.
出处
《飞行力学》
CSCD
北大核心
2010年第2期59-62,共4页
Flight Dynamics
关键词
巡飞器
SST
k-ω湍流模型
数值模拟
气动特性
loitering aerial vehicle
SST k-ωturbulence model
numerical simulation
aerodynamic characteristics
