摘要
对吸气式高超声速飞行器而言,物面热流和摩阻的准确预测对飞行器设计及安全十分关键.介绍采用CFD准确预测气动力和气动热的方法,包括流动的控制方程、湍流模型及湍流的先进壁面函数边界条件,介绍流动的数值求解方法.对典型超声速层流和湍流流动的摩擦阻力和热流进行详细的验证与确认,考察CFD工具在使用先进壁面函数边界条件后,湍流计算的法向网格无关性能力.对设计的一种吸气式高超声速飞行器的气动力和气动热进行数值模拟,为飞行器的气动设计及热防护提供了可靠的数据.
A method using CFD technology is used for accurate prediction of aerodynamic force and heat of air-breathing hypersonic vehicles. It includes governing equations, turbulence models, advanced wall boundary condition and transition formulas. Heat flux and skin friction for typical laminar and turbulent flows of air - breathing vehicles are validated. Independence of heat flux and skin friction prediction with normal grids in turbulence flow is confirmed using wall function boundary. Aerodynamic heat and force of a designed air-breathing vehicle are simulated. Reliable numerical data for vehicle aerodynamic design and aerodynamic heat protection are provided.
出处
《计算物理》
CSCD
北大核心
2008年第5期555-560,共6页
Chinese Journal of Computational Physics
基金
863高超声速飞行技术研究基金(2005AA723041)资助项目
关键词
吸气式高超声速飞行器
气动力
气动热
数值模拟
air-breathing hypersonic vehicle
aerodynamic force
aerodynamic heat
numerical simulation
