The standard Rebuild function of Rhino is not accurate enough, so Im using Grasshopper instead. When exporting an airfoil from Xfoil and then importing it into Rhino, a lot of Control Points (CP) are created (more or less 100). Of the maximum camber at a coefficient of lift (Cl) value of 0.3. Interpolate curve automatically with fewest control points using a MaxDev tolerance. The values for the constants r, k 1 and k 2/k 1 are tabulated for various positions There are also different equations for standard and reflex camber lines. For instance if the control point were closer to the root you would have that aerodynamic fillet you desire.
#Rhino airfoil generator series
The equation for the camber line is split into two sections like the 4 digit series but the division between the two sections is not at the point of maximum camber. Modifying the location of that control point, adding additional airfoil profiles, etc, will change the shape of the wing.
Export airfoil directly to a part in CATIA V5. Export airfoil directly to a Rhinoceros drawing. Elliptical airfoils Joukowsky airfoils CAD Export Features (depending on version): Export airfoil directly to a selected sketchplane in SolidWorks.
#Rhino airfoil generator generator
The maximum thickness as percentage.In the examble XX=12 so the maximum thickness is 0.12 or 12% chord. NACA 6-Series Generator The popular 'Deformable camber/thickness' geometry generator. In the examble P=3 so maximum camber is at 0.15 or 15% chordÄ = normal camber line, 1 = reflex camber line But such a model will not be close enough to actual airfoil/hydrofoil sections for technical purposes. The position of maximum camber divided by 20. It is possible to create a single span surface which looks like an airfoil/hydrofoil, and such a model may be good enough for illustrations or animations. It indicates the designed coefficient of lift (Cl) multiplied by 3/20. NACA 5 digit airfoils in the database NACA 22112 NACA 23012 NACA 23015 NACA 23018 NACA 23021 NACA 23024 NACA 23112 NACA 24112 NACA 25112 Design coefficient of lift