| 小展弦比三角翼非线性气动计算 |
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| 引用本文： | 王国明. 小展弦比三角翼非线性气动计算[J]. 合肥工业大学学报(自然科学版), 1988, 0(3) |
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| 作者姓名： | 王国明 |
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| 摘 要： | 本文采用非线性涡格法,计算定常不可压缩无粘流中锐前缘小展弦比三角平板翼的自由涡迹和气动特性。为了加快涡迹收敛,采用变松弛因子调整自由涡线的方向、在迭代中不断改变松弛顺序等方法。在4.03°～20.50°的攻角范围内机翼法向力系数和压力中心位置的计算结果与实验值符合较好;本文采用的计算方法较之其他计算方法大大减少了计算量,可作为工程上计算前缘分离机翼气动特性的一种可行方法。
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| 关 键 词： | 前缘涡 非线性气动计算 涡格法 |
THE NONLINEAR AERODYNAMIC COMPUTATION ON A DELTA WING OF SMALL ASPECT RATIO |
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| Wang Guoming. THE NONLINEAR AERODYNAMIC COMPUTATION ON A DELTA WING OF SMALL ASPECT RATIO[J]. Journal of Hefei University of Technology(Natural Science), 1988, 0(3) |
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| Authors: | Wang Guoming |
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| Affiliation: | Wang Guoming |
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| Abstract: | In this paper the nonlinear vortex-lattice method is used to compute the force-free wake and the aerodynamic characteristics of flat delta wing with small aspect ratio and sharp leading edge in steady, incompressible inviscid flows.In order to ensure rapid convergence of the force-free wake we adjust the directions of free-vortex segments by varioble rclaxaation parameter and continuously change the sequence of relaxation adjusting in iterative pro-cedure etc. The numerical results of normal-force coefficients and centres of presure agree with the experimental data in the range of angles of attack from 4.03 deg. to 20.50 dcg. The method supplied in this paper is feasible to compute the aerodynamic characteristics of the wing with separation at the leading edge in engineering due to great decpeasc in amounts of computation. |
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| Keywords: | leading-edge vortex nonlinear aerodynamic computation vortex lattice method. |
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