I need to come up with the information I need to feed in to profili 2 to be able to print out templates for the orgiional Bridi 60 size Kaos wing. Thanks in advance.

Mike, I don't have a Kaos 60; but the Kaos 40 I think would have a similar airfoil. The 40 has a semi-symmetrical foil with a max thickness of 18% at both the root and tip chords.  If you have the foil outline at the fuselage (wing root), I would first draw the chord line (line between the LE and TE), then measure the mean height (distance between the upper and lower airfoil surfaces near the max foil thickness.  Next neasure the vertical distance between this mean point and the chord line.  Convert that dimension to a percentage of the chord length (divide the chord length into this value).  That represents the airfoil camber in percent of chord length.  Go to the website below or any of the others  that airfoil data offsets for the four-digit NACA Series.  This series lists airfoils by max camber, location of max camber and max thickness (see example below).  Values of max camber and max thickness are shown as a percent of airfoil chord.  The value for the position of max camber is given as 1/10th of the actual percentage of the chord; therefore, an airfoil designated as NACA2418 would have a max camber of 2%, located at 40% and a max thickness of 18%.  ONce you know the NACA number, you can plot it using your plotter program.  Or you could also plot it my hand using the tables included in the website.  Using the tip chord length, the tip foil could be determined the same way.  In most cases, the exact airfoil is not critical.  Sorry for the long answer.  Hope this helps.

Oops....The website I mentioned for the NACA airfoil data is http://www.pdas.com/sections45.htm</p>

Ok, I'll answer the question myself. NACA 0014