idrag output file
asample2                                                                
    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   0.9975   0.7481
    2   0.0500   0.0750   0.0000   0.9874   0.7405
    3   0.0500   0.1250   0.0000   0.9668   0.7251
    4   0.0500   0.1750   0.0000   0.9352   0.7014
    5   0.0500   0.2250   0.0000   0.8913   0.6684
    6   0.0500   0.2750   0.0000   0.8330   0.6248
    7   0.0500   0.3250   0.0000   0.7571   0.5678
    8   0.0500   0.3750   0.0000   0.6571   0.4928
    9   0.0500   0.4250   0.0000   0.5179   0.3885
   10   0.0500   0.4750   0.0000   0.2180   0.1635

    0.77612 = actual lift coefficient
    -.25871 = actual moment coefficient
    0.02847 = induced drag coefficient
    1.01005 = span efficiency factor