摘要
为了在Reynolds-averaged Navier-Stokes(RANS)方程计算中耦合eN方法进行转捩判断,在RANS方程求解过程中耦合求解了可压缩层流边界层方程为判断转捩提供了精确、可靠的边界层信息。利用等熵关系由RANS方程求出的物面压力分布确定边界层外边界的速度分布,进一步确定出边界层外边界。边界层方程的求解使用Keller提出的二阶BOX方法。为了验证方法求解边界层方程的正确性,在低速流动状态下将计算结果和XFOIL的计算得到的边界层解进行了比较,二者吻合较好。
In this paper, the compressible laminar boundary- layer equations are solved in Navier- Stokes equations for airfoils which offer exact and reliable boundary- layer information for e^N transition prediction method coupling to the Navier- Stokes equations. The mathematical model of the boundary- layer equations is a two- point boundary value problem, so the boundary value must be confirmed firstly. In this paper, the isentropic relation formula is utilized for calculation of the boundary layer edge velocity distribution from the wall pressure distribution calculated by the Reynolds- averaged Navier- Stokes equations. Keller＇s BOX methods are used to solve the boundary- layer equations. The computational results are compared to the XFOIL data under the low speed flows.
出处
《航空计算技术》
2008年第2期10-13,共4页
Aeronautical Computing Technique
基金
国家重点实验室基金(9140C4201020602)
