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基于前后掠鸭式布局的简化模型,通过求解雷诺平均N-S方程,模拟了前后掠鸭式布局的绕流结构,得到了不同布局下鸭翼的升力系数曲线。通过空间流线图,分析了单独鸭翼漩涡的发展特点,以及不同布局中鸭翼涡与机翼前缘涡的干扰机理。结果表明:在后掠翼鸭式布局中,鸭翼涡在大迎角时受到机翼前缘涡的有利干扰,增大了鸭翼的升力系数,提高了失速迎角;在前掠翼鸭式布局中,鸭翼的最大升力系数有所提高,失速迎角基本保持不变。
Based on the simplified model of the front-rear razor-duck layout, the lift-coefficient curve of the canard wing under different layouts was obtained by solving the Reynolds-averaged N-S equation and simulating the flow around the razor-duck layout. Based on the spatial flow chart, the development characteristics of single duck wing swirl and the interference mechanism between duck wing vortex and wing leading edge vortex in different layouts are analyzed. The results show that in the swept-back duck-duck layout, the duck wing vortex is favorably disturbed by the leading edge vortex at high angle of attack, which increases the lift coefficient of the duck wing and raises the stalling attack angle. Style layout, the maximum lift coefficient of the canard wing has been improved, stalling attack angle remains unchanged.