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为了研究三角形小翼安装角(β)对前缘分离涡旋涡特性的影响,首先以某三角翼飞行器为研究对象,验证了数值方法的可靠性;其次选取了5个典型的小翼安装角:β=10°、15°、20°、25°、30°,分析了前缘分离涡在翼面上的流动情况及横截面上流线的拓扑点随安装角的变化规律;并分析了小翼下游旋涡强度及径向运动轨迹随安装角的变化规律,结果表明:在小翼下游X/H<20(X为流向距离,H为小翼高度)时旋涡强度随安装角增大而增大,X/H=20-80时,β=25°旋涡强度最大,X/H>80时,β=20°旋涡强度最大。
In order to study the influence of mounting angle (β) of triangular winglets on the vortex characteristics of the leading edge separation, the reliability of the numerical method is verified by taking a triangular-wing aircraft as the research object. Secondly, five typical winglets are selected: β = 10 °, 15 °, 20 °, 25 ° and 30 ° are used to analyze the flow of the leading edge vortex on the airfoil and the topological points of the streamlines along the cross section. The results show that the vortex strength increases with the installation angle when the X / H <20 (X is the flow distance and X is the winglet height) downstream of winglets When X / H = 20-80, the vortex intensity of β = 25 ° is the largest, while that of β = 20 ° is the largest at X / H> 80.