摘要
随着兵器发射技术和空气动力学技术的发展,动能弹的发射初速和飞行状态正从超声速向高超声速发展,由此产生了气动热问题.准确预测动能弹温度场是其气动力和热防护设计的关键技术.采用CFD预测温度场的方法,包括平衡流流动控制方程及差分格式,构造平衡流通量Jacob矩阵,在差分格式矢通量分裂过程中嵌入平衡流真实气体模型模拟温度场,获得平衡流气体状态方程.对典型高速动能弹热环境进行验证,考察方法的合理性.对设计的一种新型高超声速动能弹温度场进行数值模拟,为其气动设计及热防护提供了较可靠的数据.
A method with CFD technology is used for accurate prediction of temperature field of supersonic and hypersonic kinetic energy projectiles.It includes equilibrium flow governing equations and difference scheme,equilibrium flow Jacobian matrixs and equilibrium gas state equations.A real gas equilibrium air model is used to calculate temperature in vector flux split in a difference scheme.Thermal environment for typical high-speed kinetic energy projectile is validated.Rationality of the method is considered.Temperature field of a designed hypersonic kinetic energy projectile is simulated.Reliable numerical data for projectile aerodynamic design and aerodynamic heat protection are provided.
出处
《计算物理》
EI
CSCD
北大核心
2010年第6期861-868,共8页
Chinese Journal of Computational Physics
基金
"十一.五"国防预研项目
关键词
超声速
高超声速
动能弹
气动热
数值模拟
supersonic
hypersonic
kinetic energy projectile
aerodynamic heat
numerical simulation
