| 翼型周线布线性涡的有限基本解法 |
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| 引用本文： | 王振羽. 翼型周线布线性涡的有限基本解法[J]. 北京航空航天大学学报, 1993, 0(1): 118-123 |
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| 作者姓名： | 王振羽 |
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| 作者单位： | 北京航空航天大学流体力学研究所 |
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| 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。
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| 关 键 词： | 空气动力学 不可压缩流动 翼型 |
A METHOD FOR AERODYNAMIC CALCULATION BY PLACING LINEAR VARI-STRENGTH VORTEX PANELSON AIRFOIL CONTOUR |
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| Wang Zhenyu. A METHOD FOR AERODYNAMIC CALCULATION BY PLACING LINEAR VARI-STRENGTH VORTEX PANELSON AIRFOIL CONTOUR[J]. Journal of Beijing University of Aeronautics and Astronautics, 1993, 0(1): 118-123 |
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| Authors: | Wang Zhenyu |
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| Affiliation: | Fluid Mechanics Institute |
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| Abstract: | 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. |
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| Keywords: | aerodynamics incompressible flow panel method airfoil overdetermined linear equations least-square method. |
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