使用GAO-YONG方程组对不可压转捩/湍流平板边界层的计算  

The Calculation of Incompressible Wall Boundary Layer Using GAO-YONG Turbulence Equations

作　　者：陈广业[1] 高歌[1] 尹幸愉[1] 

机构地区：[1]北京航空航天大学动力系,北京100083

出　　处：《航空动力学报》2003年第1期2-7,共6页Journal of Aerospace Power

摘　　要：与以往的湍流模型不同的是GAO-YONG不可压湍流控制方程组不需要任何经验系数及壁面函数。本文运用SIMPLE方法QUICK格式求解GAO-YONG方程组,对二维零压力梯度下平板转捩/湍流边界层进行了数值模拟。结果表明,方程不仅对于边界层流动的各项细节(如表面摩擦系数Cf,对数律,亏损律等)能作出良好的预测,成功地解决了以往一般模型不能同时计算近壁区和远壁区的难题,而且能够预报层流-湍流转捩过程。本文还对机械能方程如何影响边界层近壁区特性进行了数值研究。Unlike widely used turbulence models, the GAO-YONG equations use no empirical coefficients or wall functions. In this paper, two-dimensional, stationary, and incompressible transitional/turbulent boundary layer with zero pressure gradient is numerically simulated with GAO-YONG turbulence model. Employing staggered grid arrangement, an incompressible SIMPLE code with a second-order QUICK scheme is used. The calculation successfully simulates the flow and predicts the fundamental properties of the boundary layer such as Cf, the log law, and the defect law, etc, which are close to the experimental data. All the results further verify the adaptability of the equations to real turbulent flow.

关 键 词：航空推进系统 航天推进系统 湍流 GAO-YONG理性方程 二维不可压平板边界层 转捩 

分 类 号：O357.5[理学—流体力学]