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.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1993年第1期118-123,共6页
Journal of Beijing University of Aeronautics and Astronautics
关键词
空气动力学
不可压缩流动
翼型
aerodynamics, incompressible flow, panel method, airfoil, overdetermined linear equations, least-square method.
