摘要
在耦合雷诺平均Navier-Stokes(RANS)方程求解可压缩层流边界层方程的基础上,求解了线性稳定性Orr-Sommerfeld方程,得到不同频率扰动在翼型边界层内沿弦向的放大因子N,进而采用eN转捩判断方法判断出流动转捩的位置。通过上述方法,实现了考虑转捩影响的翼型粘性绕流的雷诺平均Navier-Stokes方程数值求解,提高了翼型气动特性计算的精度。使用文中方法分析了翼型NACA63A015和NLF416的转捩点位置以及气动特性,与实验测得的结果进行比较验证了该方法的可靠性。
Without considering the transition information in the simulation of flow around airfoils, accurate aerodynamic characteristics could not be obtained. We used the full, not the simple, e^N transition prediction method to couple with the Navier-Stokes solver in order to improve the calculation accuracy. In section 1, we pointed out that three codes including the RANS code, the laminar boundary layer code and the linear stability code were needed to accomplish the flow transition prediction. In section 2, a method similar to Refs [10] and [11] was introduced to couple the three codes. First, the RANS solver provided the wall pressure coefficient cp for solving the laminar boundary layer equations. Then, we used the linear stability code to analyze the laminar boundary velocity profiles, and find out the transition point with the e^N method. Finally, we returned the transition information to the solution of RANS equations. Repeating the above process, the flow transition point can be detected automatically. We take airfoils NACA64A015 and NLF415 as our numerical examples. Figs. 3, 4 and 5 show preliminarily that our computed results are in good agreement with experimental data.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2009年第3期294-299,共6页
Journal of Northwestern Polytechnical University
基金
国家级重点实验室基金(9140C4201020602)
国家高技术研究发展计划(2007AA05Z448)资助
