三角翼大迎角流场结构和气动力特性的计算分析研究

采用数值计算方法对亚音速三角翼纵向及带有小侧滑和横侧小扰动情况下的流场结构进行了计算，利用数值计算所得到的大迎角流动流场数据，结合相关的实验研究结果，建立了对大迎角旋涡流场结构进行定量分析的方法．给出了三角翼大迎角情况下相应的气动力、力矩系数，以及机翼前缘分离涡轴线位置和旋涡破裂位置随迎角的变化规律，并对带有小侧滑和横侧小扰动情况下对横侧力矩的影响进行了计算与分析．计算结果表明，在前缘分离涡破裂前的上游旋涡区内，前缘分离涡轴线基本保持为直线，且随着迎角增加，前缘分离涡轴线位置愈靠近翼根，并远离翼面；在前缘分离涡破裂的初始阶段，于旋涡轴线处，压力系数会迅速增加，沿涡轴线方向速度迅速减小，在垂直于流向的截面内，愈靠近涡轴线处，沿涡轴线方向速度愈小，甚至出现负值，说明沿涡轴线方向出现回流．当绕机翼上表面前缘分离涡破裂后，将会导致横侧运动不稳定，如果受到小扰动，将产生横侧力矩发散．

Computation of Field Structure and Aerodynamic Characteristics of Delta Wings at High Angles of Attack

A numerical investigation of the structure of the vortical flowfield over delta wings at high angles of attack in longitudinal and with small sideslip angle is presented.Three_dimensional Navier_Stokes numerical simulations were carried out to predict the complex leeward_side flowfield characteristics that are dominated by the effect of the breakdown of the leading_edge vortices. The methods that analyze the flowfield structure quantitatively were given by using flowfield data from the computational results. In the region before the vortex breakdown, the vortex axes are approximated as being straight line. As the angle of attack increases, the vortex axes are closer to the root chord, and farther away from the wing surface. Along the vortex axes, as the adverse pressure gradients occur, the axial velocity decreases, that is lambda is negative, so the vortex is unstable, and it is possible to breakdown. The occurrence of the breakdown results in the instability of lateral motion for a delta wing, and the lateral moment diverges after a small perturbation occurs at high angles of attack. However, after a critical angle of attack is reached, the vortices breakdown completely at the wing apex, and the instability resulting from the vortex breakdown disappears.