GrabCAD 模型信息
Inventor NACA 4-digit airfoil calculator · 模型 50426
Generates a spline of the airfoil for a NACA 4-digit airfoil. This file is only compatible with Autodesk Inventor. (It may be opened in other CAD systems but the calculation is unlikely to work.) To calculate the the airfoil, change only the "Key" parameters M, p, XX, and Chord in the user parameters section. These parameters represent the components of the NACA-MPXX designation. Where: M is the maximum camber divided by 100 p is the position of the maximum camber divided by 10 XX is the thickness divided by 100 Chord is the length of the airfoil in the desired units. For 0 camber use a very small number such as 0.0001. Using "0" causes an error. It is setup for an open trailing edge with a4 = -0.1015. For a closed trailing edge change: a4 = -0.1036 Two versions are supplied: Version one is "NACA 4-DIGIT AIRFOIL.ipt" It plots the airfoil with 12 points ahead of the maximum camber and 6 points aft of the maximum camber. All points are spaced according to a cosine function so that the points are closer together towards the leading edge. The airfoil is plotted with a single interpolation spline and is fully constrained. Do not add points. Do not activate any handles, curvature, flats, or adjust tension etc. The only seams are at the flat trailing edge. Version two is "NACA 4-DIGIT AIRFOIL USING EQUATION CURVE.ipt" It plots the airfoil using 4 equation curves. While the parameter table is much simpler, the equations for the curves are very complex. It also doesn't seem to be as accurate. Especially for small airfoils. There are seams at the intersections of the 4 equation curves. The initial settings are for a NACA-3412 which has a 3% total camber, 40% camber position, a 12% thickness, and a chord of 1 inch. The spline has an open trailing edge that is closed with a short line segment so that it could be extruded into a wing shape. Refer to: http://airfoiltools.com/airfoil/naca4digit I've included a tapered sample wing. It has the base wing, development. all the individual parts, and finally the assembly. Since each part is derived from the base airfoil, changes to the airfoil profiles or base wing are automatically carried through all parts and the assembly.
- 格式
- Autodesk Inventor、Text file、Rendering
- 分类
- Aerospace、Aviation、Hobby
- 标签
- airfoil、4-digit、naca
- 数据更新
- 2026-10-02T00:22:57Z
