Calculated reentry aerodynamic heating effects on the external skin of an ICBM reentry test vehicle having a relatively low weight-to-drag ratio are presented in this report. The vehicle is a blunt cone with the aft portion designed to fail just after maximum heating and the forward portion designed to survive to impact. The tape-wound, reinforced plastic heat shield is subjected to maximum reentry heating rates between 1,250,000 and 6,500,00 kcal/sq m hr. Resulting external and internal surface temperature histories are given. Effects of extreme trajectory, vehicle characteristics, and atmosphere variations on the aluminum substructure temperature histories are discussed. (Author).