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.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
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
关键词
结冰
多段翼型
多块网格技术
有限体积法
N—S方程
icing, multi-element airfoil, multi-block grid technique, N-S equations, finite volume method
