摘要
用GAO-YONG可压缩湍流方程数值模拟了Delery管道凸起跨音流场中的激波湍流边界层干扰现象,分析了GAO-YONG可压缩湍流方程组对湍流的非平衡、多尺度、各向异性等特性的描述能力。计算中对流项、扩散项分别采用二阶ROE格式和二阶中心差分格式离散,并用多步Runge-Kutta显式时间推进法求解了空间离散后的控制方程。计算很好地模拟到了压力平台区、"λ"波结构等典型激波湍流边界层干扰的流动现象,也得到了壁面压力分布、平均速度剖面以及雷诺应力分布等,并与相应的实验数据进行了对比分析,两者符合很好。
Numerical simulations of Shock-wave turbulent boundary-layer interaction on Delery＇s bump using GAO- YONG compressible turbulence equations are presented. Properties of turbulent flow, such as muhiscale, nonequilihrium and anisotropy in GAO- YONG turbulent equations have been analyzed. Convection terms and diffusion terms are calculated using ROE （flux difference splitting） scheme and CD （center difference） scheme respectively. The Runge- Kutta time marching method is employed to solve space discrete control equations. Typical flow features are described well in simulation, such as pressure platform in separation zone, A flow structure. Meanwhile, calculations accurately predict distribution of pressure on the bump wall, mean velocity profiles and turbulent shear stress. Good agreements between the calculations and experiment are obtained.
出处
《航空计算技术》
2011年第4期40-44,共5页
Aeronautical Computing Technique
关键词
激波边界层干扰
湍流
跨音流动
GAO—YONG可压缩湍流方程组
shock - wave turbulent boundary - layer interaction
turbulent flow
transonic flow
GAO -YONG compressible turbulent equations
