idrag input file
asample1 - a linear load distribution
1                 input mode
1                 write flag
1                 symmetry flag
1                 load flag
0.                x cg position
0.25              center of pressure for airfoil sections
0.15              reference area
0.15              reference chord
1                 number of panels
0   0   0         x,y,z for 4 corners of panel 1
0   0.5 0
0.2 0.5 0
0.2 0   0
10                number of vortices for panel 1
0                 vortex spacing for panel 1
2                 number of loads for panel 1
0 1               load station 1, load 1, for panel 1
1 0               load station 2, load 2, for panel 1
