结冰对翼型和多段翼型绕流及气动特性影响研究  

Icing Research on Airfoil and Multi-Element Airfoil Based on Flow Field and Aerodynamic Performance

作　　者：桑为民[1] 李凤蔚[1] 施永毅 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中航一集团第一飞机研究院上海分院

出　　处：《西北工业大学学报》2005年第6期729-732,共4页Journal of Northwestern Polytechnical University

基　　金：西北工业大学"英才培养计划"资助

摘　　要：对翼型结冰问题,在结冰条件下,利用数值方法分析研究翼型和多段翼型绕流流场及气动特性的影响。对于翼型和多段翼型,采用分区多块网格技术,结合法向外推的代数方法和求解椭圆型方程方法,生成高质量计算网格。采用中心有限体积法,以及Runge-K utta显式时间推进格式,结合B-L代数湍流模型,运用流场分区求解算法,完成了绕流流场的N-S方程数值模拟,进一步针对3种不同的冰型:钝头体、双角体和尖头体冰型,分析不同形状的冰型对翼型和多段翼型绕流流场及气动特性的影响。Ice accretions over critical aerodynamics surface cause significant degradation in aircraft performance and handling qualities. Numerical simulations using the N-S equations are presented to investigate the effect of different ice shapes on the aerodynamic performance of airfoil and multi-element airfoil. In the icing research, we construct three different ice shapes： sharp-angled ice, blunt nosed ice and double horn ice. Using these icing models, we calculate and analyze the flow field and aerodynamic characteristics of a wing airfoil and a four-element airfoil. Solving the elliptic equations together with an algebraic method marching along the normal-to-wall direction, we generate computational grids. For the multi-element airfoil, we use a multi-block grid technique. We solve N-S equations with a conventional algorithm, which includes the cell-centred finite volume method and the Runge-Kutta time-stepping scheme. We complete the solution of N-S equations by introducing the Baldwin-Lomax algebraic turbulence model that can predict the attached and little-separation flows. The calculated results are in good agreement with experimental data and show preliminarily that our method of icing research is feasible.

关 键 词：结冰 多段翼型 多块网格技术 有限体积法 N—S方程 

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]