The present paper proposes a novel means of heat dissipation in high speed flows where shock waves are formed by transferring heat along shock wave without transferring heat to body itself. This may be achieved through controlled oscillation of the shock wave without making it and the flow surrounding it unstable. From an experimental investigation on a 1/30 scale Apollo module using the supersonic wind tunnel at the Aerodynamics Laboratory of the University of New South Wales at Mach 3, counter flow jet injection and deploying into upstream flow behind the detached bow shock wave are formed to examine this concept. Results obtained are very promising and provide clear evidence to support this concept. The findings have the potential of achieving heat reduction with lower energy requirement. A greater understanding of the various interacting flow mechanism and optimization of different design parameters may open up the possibility of incorporating the concept into a viable and cost effective thermal protection systems for high speed vehicles.