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本文提出一种计算模型,用以计算亚声速大迎角下前缘分离机翼的流动和气动特性。通过在涡轴上分布线涡/线汇,这种计算模型包括了对前缘自由涡面、涡核及涡的卷吸作用的模拟。由于它是在非线性离散涡法的基础上发展起来的,因而具有计算过程简捷的特点。对三角翼及双三角翼气动特性的计算表明,计算值与实验值符合得相当好。计算还表明,在计算中计及和不计及涡的卷吸作用能引起计算载荷相当大的变化。
In this paper, a computational model is proposed to calculate the flow and aerodynamic characteristics of a leading-edge separation wing at a high sub-swoon. By distributing the line vortex / sink on the vortex axis, this computational model includes a simulation of the entrainment effect of the free vortex, vortex core and vortex on the leading edge. Because it is developed on the basis of nonlinear discrete vortex method, it has the characteristics of simple calculation process. The aerodynamic characteristics of the delta wing and the double delta wing show that the calculated values are in good agreement with the experimental values. The calculations also show that taking into account and ignoring the entrainment of vortices in calculations can cause considerable changes in computational load.