An 8.0×10⁴ kg aircraft is orbiting Earth at a constant velocity. The forces acting on it are depicted in the figure below. The thrust generated by the onboard propulsion system is F_w = 7.2×10⁵N, acting on a line 1.8 m below the aircraft's center of mass. Calculate the drag force $F_D$ exerted by the atmosphere and the distance above the center of mass where it acts. Assume that both F_D and F_W are horizontal. (F_lift represents the lift force generated by the aircraft's wings, if any.)