多段翼型结冰数值模拟研究  

Numerical Simulation of Icing on a Multi-Element Airfoil

作　　者：周志宏[1] 李凤蔚[1] 李广宁[1] 张淼[2] 

机构地区：[1]西北工业大学航空学院流体力学系,陕西西安710072 [2]上海飞机设计研究院,上海200232

出　　处：《西北工业大学学报》2011年第1期133-136,共4页Journal of Northwestern Polytechnical University

基　　金：中国商用飞机有限责任公司;上海飞机设计研究院民用飞机防除冰项目资助

摘　　要：文章采用计算流体力学方法对多段翼型进行了结冰数值模拟研究。应用多块网格技术生成多段翼型网格。引入水滴流场的概念,通过求解空气-水滴两相流场的欧拉方法,获得翼型表面水滴收集特性。流场采用有限体积法及LU-SGS隐式时间推进数值求解,运用流场分区求解算法,完成了多段翼型绕流流场及水滴流场的数值求解。建立了冰层的法向增长模型,对冰形进行了预测。Ice accretion leads to significant deterioration of aircraft aerodynamic performance and handling quali- ties. In this paper, ice accretion on multi-element airfoils are predicted using CFD method. Grid generation and flow analysis methods for a multi-element airfoil are based on multi-block grid technique. This paper gives details about an Eulerian method for water impingement prediction on airfoils. Ice shape is determined with the assumption that all droplets freeze at their points of impact and the ice grows in the direction normal to the surface. The Navier- Stokes equations are used to calculate the air flow field. A time-accurate, fully implicit LU-SGS （Lower-upper Symmetric-Gauss-Seidel） method is used to solve the viscous flow problems. It uses a finite volume cell-centered formulation on structured grids and the convective terms are differenced using the flux-vector-splitting technique of Van Leer, and Spalart-Allmaras turbulence model is used in the numerical procedure. With the above methods and techniques, the computational results are in good agreement with the available experimental data, thus showing pre- liminarily that our method of icing prediction model is reliable and flow field numerical simulation is feasible.

关 键 词：多段翼型 Navier-Stoker方程 欧拉两相流 结冰 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]