前后掠翼鸭式布局中鸭翼涡的流动机理  

Flow mechanism of canard vortex over forward and backward-swept wing configurations

作　　者：张冬[1] 胡孟权[1] 王旭[1] 吴章沅 

机构地区：[1]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《飞行力学》2016年第1期36-39,45,共5页Flight Dynamics

基　　金：国家自然科学基金资助(11402301);航空科学基金资助(20110596007)

摘　　要：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 simplified models of forward and backward-swept wing configuration,numerical investigation on the vortical structure was carried out by solving Reynolds averaged Navier-Stokes（ N-S） equations,and obtained the lift coefficient curves of canard on different configurations. The characteristics of the vortex over single canard and the vortex interaction mechanisms of canard vortex and main wing vortex were analyzed by streamlines. The analysis indicates that the main wing vortex would perform a favorable impact on the canard vortex at high AOA region for backward-swept wing configuration,which enhanced the lift coefficient and increased stall angle of attack. The lift coefficient is also enhanced for forward-swept wing configuration,while the stall angle of attack remains unchanged.

关 键 词：鸭式布局 鸭翼涡 流动机理 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]