idrag output file
asample1                                                                
    1    = input mode
    1    = write flag
    1    = symmetry flag
    0.00 = design lift coefficient
    0    = moment coefficient flag
    0.00 = design moment coefficient
    0.00 = x cg position
    0.25 = center of pressure for airfoil sections
    0.15 = reference area
    0.15 = reference chord
    1    = 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

    i   x        y        z        load     cn
    1   0.0500   0.0250   0.0000   0.9500   0.7125
    2   0.0500   0.0750   0.0000   0.8500   0.6375
    3   0.0500   0.1250   0.0000   0.7500   0.5625
    4   0.0500   0.1750   0.0000   0.6500   0.4875
    5   0.0500   0.2250   0.0000   0.5500   0.4125
    6   0.0500   0.2750   0.0000   0.4500   0.3375
    7   0.0500   0.3250   0.0000   0.3500   0.2625
    8   0.0500   0.3750   0.0000   0.2500   0.1875
    9   0.0500   0.4250   0.0000   0.1500   0.1125
   10   0.0500   0.4750   0.0000   0.0500   0.0375

    0.50000 = actual lift coefficient
    -.16667 = actual moment coefficient
    0.01636 = induced drag coefficient
    0.72964 = span efficiency factor