The drag performance of truncated cones in a supersonic flow of Mach number 2 with repetitive energy depositions is evaluated by using computational fluid dynamics. The calculated result shows a quasisteady flowfield: a virtual spike, which is supported by an axi-symmetric recirculation, is formed in front of the truncated cone. The recirculation is generated due to baroclinic interaction between a bow shock wave and a heated bubble produced by energy depositions. The reduction of the drag over the truncated cone is attributed to the virtual spike so formed. The time averaged drag of the truncated cone depends on the amount of deposited energy, repetition frequency and the area of a truncation surface. The averaged drag can be smaller than that of a sharp cone with the same apex angle, maintaining the energy savings due to drag reduction.