OpenSCAD_airfoil

Parametric Airfoil and Wing generator v0.1

Homepage: https://github.com/ErroneousBosch/OpenSCAD_airfoil

For a brief overview of the math and specifications used, see https://en.wikipedia.org/wiki/NACA_airfoil

Globals:

$close_airfoils: Defines whether you want the back of your air foils closed, or if you want them open (default: false)

$airfoil_fn: number of sides for your airfoil. (default: 100)

airfoil_poly help:

This function generates a 2D polygon of an airfoil, using the following variables.

c: Chord length, this is the chord length of your airfoil. (default: 100)

naca: The NACA 4-digit specification for your airfoil. (default: 0015)

raw: overrides the NACA code with direct ratios. Provide in the same order as the NACA digits. (e.g NACA 4123 becomes raw [.4,.1,.23])

airfoil_simple_wing help:

This will generate a simple wing based on one or more supplied airfoils. Each set of airfoils is an individual shape, allowing for very complex variation along the wing.

airfoils (required): Two modes:

Single Airfoil: Specifying a single airfoil will generate a uniform wing based on that airfoil. You can specify the airfoil as a set (vector) of [chord, naca].

Multiple airfoils: Specify a set (vector) of airfoils. Individual airfoils are specified the same as a single airfoil (see above). These airfoils will be spaced evenly along the wing length.

wing_angle: a set of angles, [sweep,slope]. Sweep is along the x axis, slope along the y axis. (optional, default=[0,0])

wing_length: length of the wing (optional, default=1000)