idrag output file
winglet                                                                 
    0    = input mode
    1    = write flag
    1    = symmetry flag
    1.00 = design lift coefficient
    1    = moment coefficient flag
    0.00 = design moment coefficient
    0.03 = x cg position
    0.25 = center of pressure for airfoil sections
    0.20 = reference area
    0.20 = reference chord
    3    = number of panels

    x        y        z    for panel 1
    0.00     0.00     0.00
    0.00     0.50     0.00
    0.20     0.50     0.00
    0.20     0.00     0.00
   10    = number of vortices
    0    = vortex spacing flag

    x        y        z    for panel 2
    0.00     0.50     0.00
    0.00     0.50     0.10
    0.20     0.50     0.10
    0.20     0.50     0.00
    5    = number of vortices
    0    = vortex spacing flag

    x        y        z    for panel 3
    1.00     0.00     0.10
    1.00     0.20     0.10
    1.10     0.20     0.10
    1.10     0.00     0.10
    6    = number of vortices
    0    = vortex spacing flag

    i   x        y        z        load     cn
    1   0.0500   0.0250   0.0000   1.1867   1.1867
    2   0.0500   0.0750   0.0000   1.1756   1.1756
    3   0.0500   0.1250   0.0000   1.1534   1.1534
    4   0.0500   0.1750   0.0000   1.1205   1.1205
    5   0.0500   0.2250   0.0000   1.0784   1.0784
    6   0.0500   0.2750   0.0000   1.0287   1.0287
    7   0.0500   0.3250   0.0000   0.9709   0.9709
    8   0.0500   0.3750   0.0000   0.9041   0.9041
    9   0.0500   0.4250   0.0000   0.8292   0.8292
   10   0.0500   0.4750   0.0000   0.7574   0.7574
   11   0.0500   0.5000   0.0100   0.4581   0.4581
   12   0.0500   0.5000   0.0300   0.4496   0.4496
   13   0.0500   0.5000   0.0500   0.3795   0.3795
   14   0.0500   0.5000   0.0700   0.2967   0.2967
   15   0.0500   0.5000   0.0900   0.1938   0.1938
   16   1.0250   0.0167   0.1000  -0.0642  -0.1284
   17   1.0250   0.0500   0.1000  -0.0622  -0.1244
   18   1.0250   0.0833   0.1000  -0.0581  -0.1162
   19   1.0250   0.1167   0.1000  -0.0517  -0.1034
   20   1.0250   0.1500   0.1000  -0.0425  -0.0851
   21   1.0250   0.1833   0.1000  -0.0290  -0.0579

    1.00000 = actual lift coefficient
    0.00000 = actual moment coefficient
    0.05008 = induced drag coefficient
    1.27132 = span efficiency factor