Numerical Modeling of the Vortex/Airfoil Interaction
Numerical Modeling of the Vortex/Airfoil Interaction
复制标题
涡流/机翼相互作用的数值模拟
DOI：
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发表时间：
1987
期刊：
影响因子：
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通讯作者：
A. Panaras
中科院分区：
文献类型：
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作者：
A. Panaras
提出了一种考虑真实旋涡有限面积的旋涡/翼型干扰模型。采用了两种旋涡模型。首先，涡量层的扰动部分由四排小强度的离散涡旋模拟。在第二种情况下，多个离散的旋涡排列在一个圆内。第一个模型可以模拟剪切层或尾迹，第二个模型可以模拟结构良好的涡旋。该方法已用于计算干扰涡对翼型表面的压力。这两个模型产生了相似的结果。结果表明，当旋涡距翼型表面距离较大时，旋涡的有限面积不是决定诱导压力场的重要因素。然而，当涡距表面的距离减小时，其形状会发生变形，诱导出的压力脉冲的幅度比等效点涡所产生的压力脉冲的幅度要小。在撞击翼型前缘的极限处，涡流被一分为二，与时间相关的压力系数在某些时间间隔甚至出现负值。
A modeling of the vortex/airfoil interaction is presented, in which the finite-area of the real vortices is taken into consideration. Two vortex models are used. In the first, a disturbed piece of a vorticity layer is simulated by four rows of discrete vortices of small strength. In the second, a number of discrete vortices is arranged within a circle. The first model may simulate a shear layer or a wake and the second a well-formed vortex. The method has been applied to the calculation of the pressure induced on the surface of the airfoil by the interacting vortex. Both models yield similar results. It has been found that when the distance of the vortex from the surface of the airfoil is large, the finite-area of the vortex is not a significant factor in determining the induced pressure field. However, when the distance of the vortex from the surface is reduced, its shape is distorted and the inducedpressure pulses have lower amplitude than those induced by an equivalent point vortex. At the limit, where it impinges on the leading edge of the airfoil, the vortex is split in two and the time-dependent pressure coefficient takes on even negative values at some time intervals.