Airfoil Tools
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Airfoil plotter (naca0006-il)

NACA 0006 - NACA 0006 airfoil

Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. The dat file data can either be loaded from the airfoil database or your own airfoils which can be entered here and they will appear in the list of airfoils in the form below.


Airfoil plot (naca0006-il)
Choose from database list or add you own airfoils here.
Chord width in millimetres. (1 inch = 25.40mm)
Radius of camber in millimetres, Zero for no curve
Thickness adjustment.100% is normal thickness. 50% is half. 200% is double
Adjust the position of the origin e.g. 50% is mid chord
Pitch or angle of attack. 180 flips the plot
Line parallel to airfoil for wing covering or jig. Negative values are external, positive internal.
Plot a mirror image
Print the airfoil data on the image
Show camber line on image
X grid size in millimetres
Y grid size in millimetres
Used for printing plan. A4 landscape approx 280mm
Used for printing plan. A4 landscape approx 180mm

Please refer to the information page for details of how the dat files are parsed and any parser warnings that appear in the form above.

Plotter transformations

The tranformations are applied in the following order.

  1. Thickness - The dat file Y coordinate is multiplied by the thickness / 100
  2. Reverse - If the reverse tick box is set the Y coordinate is reversed (Y = -Y) to invert the image about the X axis
  3. Origin - The X coordinate is adjusted to move the position of the origin (X = X - (origin / 100) )
  4. Chord width - The X and Y coordinates are multiplied by the chord width to convert the values to millimetres
  5. Radius - If the radius is non zero the X and Y coordinates are transformed around a circle with a centre at X=0 and Y=(radius value)
  6. Pitch - The X and Y coordinates are rotated about the origin by the pitch angle.