Draws an airfoil profile based on standard NACA 4-digit specifications.
Maximum camber (m):
Defines how much height (vertically) is between the chord line and camber line at point p, in tens of %.
For example, a value of 2 means at 20% of the chord line (X coordinate as 0.2)
Camber position (p):
Point (in tens of %) of the chord line where the camber offset is highest with respect to the center (zero) line.
For example, a value of 4 means at 20% of the chord line, the distance from chordline to camber is highest (vertically).
Thickness (t):
Defines how thick the airfoil is, in % of the chord line at the position of maximum camber. This is measured
perpendicular to the slope of the camber line at a given point.
Camber line (●)
The airfoil surface will be "symmetric" around this curved line (perpendicular to the slope at a given point).
Airfoils without camber (e.g. where the camber line equals the chord line, the wing is "flat") it will be
called a symmetric airfoil (at which point I believe there is no lift when the airfoil is not angled up).
Chord line (●)
Straight line from the front point to the end point of the wing.
Note: You can extract the SVG from the HTML code and import it into i.e. Inkscape
to prepare it for for (3D) printing. See OpenSCAD for how to convert it into a 3D shape.