翼型周线布线性涡的有限基本解法  

A METHOD FOR AERODYNAMIC CALCULATION BY PLACING LINEAR VARI-STRENGTH VORTEX PANELSON AIRFOIL CONTOUR

作　　者：王振羽[1] 

机构地区：[1]北京航空航天大学流体力学研究所

出　　处：《北京航空航天大学学报》1993年第1期118-123,共6页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：在翼型周界线上布线性变强度分布涡,在一定边界条件下建立求解涡强度的线性方程组。经过试探,确定了比较合适的控制点位置。为满足库塔条件而令后缘处涡强度为零,但导致了方程组的矛盾性。采用最小二乘法求解矛盾方程组,可获得误差最小的唯一解。本方法简便,易于应用。计算结果与试验值或精确解相比,有良好的准确性,可用于一般工程计算。Linear vari-strength vortex panels are placed on the contour of airfoil. The system of linear equations determining the vortex strength is derived under specific boundary condition. The ap-proriat control point location is found by cutting ard trying. The system becomes overdetermined as zero vortex strength is set at trailing edge,to make the Kutta condition be satisfied. A technique for sieving the overdetermined system is gived by utilizing least-square method and the u-nique solution with minimum-error is obtained. The technique is simple and facile for application. The comparing of the calculation results with experimental date and exact solution indicates that the technique possess a certain exactitude, and can be applied to engineering calculation and design.

关 键 词：空气动力学 不可压缩流动 翼型 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]