CreateAirfoil ( AirfoilType, PointCount, arrParams, ClosedFlag )

Geometry Card
Arguments AirfoilType the type of airfoil to create. One of:
  0 — NACA 4-digit airfoil
parameter[0] = relative thickness t/c
parameter[2] = relative camber f/c
parameter[3] = location of maximum camber xf/c

1 — NACA 4-digit airfoil, modified, uses parameters [0,1,2,3,4]
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = relative camber f/c
parameter[3] = location of maximum camber xf/c
parameter[4] = leading edge radius

2 — NACA 5-digit airfoil
parameter[0] = relative thickness t/c
parameter[2] = design lift coefficient Cl
parameter[3] = location of maximum camber xf/c

3 — NACA 5-digit airfoil, modified
parameter[0] = relative thickness t/c
parameter[2] = design lift coefficient Cl
parameter[3] = location of maximum camber xf/c

4 — NACA 07-series airfoil
parameter[0] = relative thickness t/c
parameter[2] = design lift coefficient Cl

5 — NACA 16-series airfoil
parameter[0] = relative thickness t/c
parameter[2] = design lift coefficient Cl

6 — NACA 6-series airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = design lift coefficient Cl
parameter[3] = camber type a = 0.1 ... 1.0
parameter[4] = toggle switch: if > 0 : apply "A" modification

7 — TsAGI series "B" airfoil
parameter[0] = relative thickness t/c

8 — NPL EQH airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = relative camber f/c
parameter[3] = location of maximum camber xf/c
parameter[4] = toggle switch: if > 0 : apply "H" modification

9 — NPL EQH airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = relative camber f/c
parameter[3] = location of maximum camber xf/c
parameter[4] = toggle switch: if > 0 : apply "H" modification

10 — symmetrical circular arc airfoil (biconvex)
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c

11 — symmetrical wedge airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c

12 — cambered plate airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[3] = location of maximum camber xf/c

13 — Van de Vooren/ de Jong airfoil
parameter[0] = relative thickness t/c
parameter[1] = trailing edge angle

14 — Newman airfoil
parameter[0] = relative thickness t/c

16 — Joukovsky airfoil
parameter[0] = relative thickness t/c
parameter[2] = relative camber f/c

16 — Helmbold-Keune airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = trailing edge angle
parameter[3] = curvature radius
parameter[4] = leading edge radius

17 — Parsec-11 airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = trailing edge angle
parameter[3] = curvature control
parameter[4] = leading edge radius

18 — Roίner airfoil
parameter[0] = relative thickness t/c
parameter[1] = location of maximum thickness xt/c
parameter[2] = trailing edge angle
parameter[4] = leading edge radius

19 — Horten airfoil
parameter[0] = relative thickness t/c
parameter[2] = relative camber f/c
PointCount the number of points defining the airfoil shape
arrParams The parameters as described above must be transferred in the form of an Array.

When there is a gap in the parameter list above (e.g. only parameter [0] and [2] are specified), the unused parameters must be supplied and should be set to zero.
  ClosedFlag whether JavaFoil should close the trailing edge (some airfoils have thick trailing edges by definition)
Description Creates an airfoil from various airfoil families according to the parameters.
Remarks While not all parameters are used for all airfoil types, at least a dummy value is required.
Performs the same action as the "Create airfoil" button.

The following example shows how to create the parameter array::

var AirfoilType = 0; // NACA 4-digit
var PointCount = 121;
var dThickness = 0.15;
var dCamber = 0.02;
var dCamberLocation = 0.40;
var params = new Array ( dThickness,0.0, dCamber, dCamberLocation );

Geometry.CreateAirfoil ( AirfoilType, PointCount, params, true );