The report describes a lumped mass computer simulation of a trailing wire system towed by an orbiting aircraft. The USAF U-10 aircraft flight conditions were used as applied to three flightpaths constant altitude circular, constant altitude elliptical, and non-constant altitude circular orbit. These flightpaths were flown in no wind and 30 knot wind conditions. Wire lengths of 4000 ft and 8000 ft were used where the free end was attached to a circular sphere of 25 and 100 lbs. The results from 12 orbiting trailing wire configurations are tabulated andor plotted. One of the main objectives in this analysis was to determine how yo-yo of the free end of the wire in wind might be alleviated or at least minimized.