Wing-tip grid reconstruction method of iced three-dimensional wing

Abstract

The invention discloses a wing-tip grid reconstruction method of iced three-dimensional wings. In the method, a virtual curve is firstly constructed; the external part of the end surface of a wing tip stretches outwards along an opening direction to form the virtual curve; the virtual curve is internally connected with the end surface of the wing tip and externally connected with a far-field plane; a wing surface and the virtual curve are both grid auxiliary curves; the grid auxiliary curves divide the computational region of the whole three-dimensional wings into two sub-regions: exterior normal direction region I of the auxiliary curves and an internal region of the auxiliary curves; and grids of the internal region of the auxiliary curves and the exterior normal direction region I of the auxiliary curves are respectively reconstructed. Using the method of the invention can popularize icing calculation into a three-dimensional space, thus being closer to the actual icing situation of a plane; and grid reconstruction with various time steps realizes three-dimensional icing step calculation and ensures precision and stability of icing calculation.

Description

technical field [0001] The invention relates to the grid generation of the wing tip end surface and other areas in the three-dimensional wing icing calculation, especially the grid reconstruction method on the complex boundary of the wing tip after the ice layer covers the wing surface. Background technique [0002] When an aircraft passes through clouds containing supercooled water droplets, icing usually occurs on the leading edge of the wings, resulting in reduced flight performance of the aircraft. In the numerical calculation of icing, it is necessary to simulate the growth process of ice layers, so it involves the problem of mesh reconstruction on the surface of the wing, that is, the mesh must be readjusted after each time step to adapt to the ice layer. complex shape of the wing. The current conventional mesh generation methods at home and abroad treat the tip of the wing as a blunt body or a streamlined body, but only the mesh around the uniced wing can be generate...

AI Technical Summary

Problems solved by technology

During the calculation process, after the ice layer on the wing surface is extrapolated, the leading edge profile of the wing tip also becomes tortuous. At this time, the conventional method will not be able to reconstruct the mesh from the wing tip to the far field area, so it will not be used in the icing calculation. adopted

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