Showing papers on "Vortex lattice method published in 1966"
01 Jan 1966
TL;DR: In this article, the authors considered wing systems that contain several wing surfaces, and the surfaces were arbitrarily divided in the chordwise and spanwise directions into panels ('boxes'), and the panel load was simulated by a horseshoe vortex, where the boundary condition was fulfilled on every panel at one point.
Abstract: : Wing systems that contain several wing surfaces are considered. The surfaces are arbitrarily divided in the chordwise and spanwise directions into panels ('boxes'). The panel load is simulated by a horseshoe vortex, and the boundary condition is fulfilled on every panel at one point. For each surface the vortices and the control points are positioned on a wing chord plane. These planes are perpendicular to the y- or z-axis. The incidence distribution or the load distribution may be found from a system of linear equations, when one of these distributions is given. The calculations can be performed for elastic wings, if the elastic properties are known in the form of a deformation matrix. The calculation procedure was programmed for an electronic computer. Good correlation was obtained between the results from this method and those from other lifting surface methods or experiments. (Author)
98 citations
01 May 1966
TL;DR: In this article, the vortex lattice method for the calculation of loads on a wing advancing in a uniform stream was extended to the case of a wing in the vicinity of infinite vortices, with the understanding that the method can be applied to more complicated cases once its convergence and its validity have been shown.
Abstract: : The vortex lattice method for the calculation of loads on a wing advancing in a uniform stream was extended to the case of a wing in the vicinity of infinite vortices. No experimental data or different treatments of the same problem being available in the literature in order to verify the accuracy of the present method, the results in the report had to be limited to checking their convergence with respect to the three parameters involved and investigating what conditions them. The problem being treated linearly, only the simple case of one infinite vortex at the midspan of a wing at zero angle of attack was tested, with the understanding that the method can be applied to more complicated cases once its convergence and its validity have been shown.
4 citations