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