摘要
整体网格变形技术对其他网格技术的使用产生影响,难以相互配合来解决复杂的流动问题。发展一套基于TFI(超限插值法)技术的局部网格变形方法,该方法不同于已有的整体网格变形思路,将网格变形控制在有限的区域内,在保证网格质量的同时,不影响其他区域的网格,因此不会对其他动网格方法的使用造成影响。以带后缘襟翼的NACA0012翼型为例,对翼型俯仰振荡耦合襟翼偏转运动的动态流场进行数值模拟,结果表明:计算结果与实验值吻合良好,证明了本文发展的局部网格变形方法的可行性。
Global mesh deformation technique has influence on other dynamic grid methods,so it is difficult to be combined with other dynamic grid methods to solve complex flow problems.A local grid deformation method based on TFI（Transfinite Interpolation）is developed.This method,which is different from other global grid deformation methods,is that it can limit the deformation in specific zones without any influence on grids of other zones,so it will not hamper the use of other dynamic grid methods.For an airfoil NACA0012 with a flap,numerical simulations of pitching oscillations are conducted,and computational results agrees well with experimental results.Then it is concluded that the method developed in this paper is viable for flow solutions of complex geometries.
出处
《航空工程进展》
CSCD
2016年第2期216-224,共9页
Advances in Aeronautical Science and Engineering
关键词
襟翼偏转
网格变形
俯仰振荡
非定常流动
超限插值法
flap deflection
grid deformation
pitching oscillation
unsteady flow
transfinite interpolation
