Spalart-Allmaras湍流模型在弧形翼超音速流场数值模拟中的应用  

Application of Spalart-Allmaras Turbulent Model in Numerical Simulation of Wrap-Around Fins' Flowfield at Supersonic Speed

作　　者：郑健[1] 周长省[1] 鞠玉涛[1] 张家仙[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《重庆工学院学报（自然科学版）》2008年第12期34-39,共6页Journal of Chongqing Institute of Technology

摘　　要：利用Spalart-Allmaras湍流模型对三角翼-身组合体绕流流场进行数值模拟,并与国外风洞试验数据进行比较,验证了此湍流模型在超音速复杂流动计算中的有效性.同时采用基于密度的隐式求解器,数值离散格式采用二阶迎风格式,对十字形布置的4片弧形尾翼弹超音速流场进行了数值模拟.数值模拟结果给出了弧形翼附近的流场结构,并对弧形翼凹凸表面的压力分布做了详细分析,得出了弧形翼在零攻角下产生升力的机理.Spalart-Allmaras turbulent model is used for the numerical simulation of projectile configuration with four wrap-around fins in supersonic speed. The simulation results are compared with the experiment data obtained from the wind tunnel abroad, and the validity of Spalart-Alhnaras turbulent model in super- sonic complicated flow is verified with DERA body-wing configuration. The implicit solver based on density is used with 2nd upwind numeric discrete scheme for the numerical simulation of supersonic flowfield of the four cross-arranged wrap-around fins. Simulation results preferably give the flowfield structure of wrap- around fin. Pressure distribution of fin＇ s surface is analyzed in detail and the mechanism of producing lift of wrap-around fin is obtained at zero angle of attack.

关 键 词：Spalart-Allmaras湍流模型 弧形翼 数值模拟 流场 

分 类 号：V211.24[航空宇航科学与技术—航空宇航推进理论与工程]