Hi All,

I am trying to make 4 airfoil shapes, to represent the 4 panels in a taped wing. I have recieved some information via email from someone who knows more than I do on this subject, but i am a little confused????

Airfoils are based on the Symetrical NACA 0012 airfoil, with the following changes:

Airfoil 1: Top 5%, Bottom 8% (inverted)
Airfoil 2: Standard NACA 0012
Airfoil 3: Top 6%, Bottom 5%
Airfoil 4: Top 6%, Bottom 2%

Airfoil 1 is the root
Airfoil 2 is the end of the first panel / start of the second panel
Airfoil 3 is the end of the second panel / start of the third panel
Airfoil 4 is the wing top airfoil

I would use Airfoil 1 at +3 degrees incidence, and Airfoil 4 at -3 degrees incidence - and airfoil 2 and 3 somewhere in between (depending on where they end up along the span).

Can anyone help me with instructions on how to make these using profili?

Also - I understand that the NACA 0012 means that the airfoil is 0% Camber at 0% of the chord, and is 12% of the chord thick at the widest part. How would I name the airfoils above?

Airfoil 1 - 13% - NACA ??13
Airfoil 3 - 11% - NACA ??11
Airfoil 4 - 8% - NACA ??08

Thanks - sorry if these are stupid questions, I am VERY new to this!!!!