Airfoil database files5/2/2024 The leading edge of each airfoil is positioned in space based on the values in the x, y, and z lists.Īn offset in the x-y plane can be added to this position with the offset array before chord scaling is applied. The position, orientation, and scaling of the airfoil sections are stipulated in lists corresponding with the original airfoil data list. The coordinates of the airfoil are contained in the file rae2822.dat. If there are a large number of sections, the number of control points needs to be increased to prevent the size of the output files from becoming unreasonably large.įor this tutorial, we use the RAE 2822 transonic airfoil as the cross-section of our wing.Ī visualization of the airfoil geometry is given on Figure 1. Note that the number of sections must match the length of all the wing geometry data lists discussed below.Īlso note that the number of control points should vary with the number of sections.įor cases with few sections, using a small number of control points yields the best results. In general, any wing will require at least 2 sections to produce a valid geometry.Īdding more sections allows more precise wing definition, which is generally necessary for matching previously defined wing geometries. The number of sections needed for a geometry generation is dependent on the intention of the geometry. The airfoil should be scaled to a unit chord with the leading edge centered at the origin. The airfoil data files can be downloaded from online or generated from a variety of software. The wing is lofted from a set of airfoils distributed along the span of the wing. Airfoil_list = * 2 naf = len ( airfoil_list ) # number of airfoils
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