AIRFOIL CONVERTER MANUAL
Version 2015-02-08

- Put your standard airfoil.dat file in the working directory (you must use exactly these name airfoil.dat)
- Edit acdata.txt to select inlets position %, and airfoil thickness amplification factor
- Run ./a.out executable in Linux (or a.exe in Windows)
- Read output file airfoil.txt and verify result matches your objective
- rename airfoil.txt file acording these especified in leparagliding.txt data file.
- Verify inlets positions in leparagliding.txt file (SECTION 2, columns 3 and 4) matches exactly with the defined airfoil(s). (*)

File acdata.txt structure:

real	integer
real	integer
real

Example:

1.6	-1
6.3	-1
1.0

Explanation:

Line 1 column 1: real (0 to 100 is % of chord inlet in)
Line 1 column 2: boolean (-1,0,+1) -1 denotes point below chord, 0 point in chord, and +1 point over chord

Line 2 column 1: real (0 to 100 is % of chord inlet out)
Line 2 column 2: boolean (-1,0,+1) -1 denotes point below chord, 0 point in chord, and +1 point over chord

Line 3: real thickness amplification (1.0 is most habitual; use 0.0 for wing tip)

Program generates also airfoil.dxf file for viewing in CAD.


(*) Coming soon is expected to integrate this small program within leparagliding, so the definition of the position of inlets is done automatically, just by reading Section 2.