摘要
采用数值模拟的方法分析了飞机背负任务系统后对横侧气动特性的影响,以及提出了平尾加端板的方式改善该情况下的横侧气动特性。在数值模拟过程中,控制方程为雷诺平均N-S方程,采用了基于非结构网格的有限体积方法。湍流模型采用了S-A方程模型。研究结果表明,飞机背负任务系统后会引起航向力矩系数在小侧滑角下变得较小而使得飞机出现横侧不稳定。为改善该类飞机的横侧特性,采用了平尾加端板的措施,数值结果表明,该措施能改善该类飞机的横侧不稳定性,使得飞机在背负任务系统后具有较好的横侧气动特性。
The longitudinal and lateral aerodynamic characteristics of the aircraft with the atop radome are studied by the numerical method and the flow mechanisms for such flows are analyzed.The governing equations are Reynolds-averaged Navier-Stokes equations solved by the unstructured finite volume method.A S-A equation turbulence model is adopted.Study results show that the radome atop aircraft has large effects on longitudinal and directional stability,and makes the aircraft possible to enter roll instability.End-plates at the end of the horizontal tails are used to improve the longitudinal and lateral stability.Numerical results show that the end-plates make the aircraft improve the longitudinal and lateral instability.This research is helpful to understand the aerodynamic characteristics and flow mechanisms of the aircraft with the atop radome,and provides a reasonable reference for atop radome aircraft design.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2010年第6期694-698,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
飞机
数值分析
横侧稳定性
端板
雷达罩
aircraft
numerical analysis
longitudinal and lateral stability
end-plates
radar radome
