摘要
机翼尾涡会严重干扰平尾流场,影响平尾的效率。通过合理的拓扑结构,多块网格技术对机翼-尾翼流场进行了网格划分,采用N-S方程有限体积法对机翼-尾翼流场进行数值模拟。计算结果验证了网格生成的有效性和计算方法的合理性。
Vortex interfere flowfield of the tail which reduce it＇s efficiency. We choose reasonable topology and multiblock technology to discretize wing-tail flowfield. N-S calculations compute wing-tail flowfield by using the finite volume method. The results prove that the are performed to grid generation is adaptable and the computational methods are precise.
出处
《机械设计与制造》
北大核心
2007年第11期4-5,共2页
Machinery Design & Manufacture
