idrag input file
winglet design
0               input mode
1               write flag
1               symmetry flag
1.0             cl_design
1               cm_flag
0               cm_design
0.03            x cg position
0.25            center of pressure for airfoil sections
0.2             reference area
0.2             reference chord
3               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
0   0.5 0       x,y,z for 4 corners of panel 2
0   0.5 0.1
0.2 0.5 0.1
0.2 0.5 0
5               number of vortices for panel 2
0               vortex spacing for panel 2
1   0   0.1     x,y,z for 4 corners of panel 3
1   0.2 0.1
1.1 0.2 0.1
1.1 0   0.1
6               number of vortices for panel 3
0               vortex spacing for panel 3