Flights in the hypersonic flow regime are only possible if the surface pressure and surface heat flux are reduced to the sustainable limits of the common materials used for designing the aircraft. Most of the computational or experimental studies available in literature are conducted at lower total temperature conditions or with perfect gas assumption. Hence, current investigation is carried out with in house developed non-equilibrium N-S flow solver which incorporates various elementary reactions of the real gas at elevated freestream stagnation enthalpy. In this context, hypersonic flow over hemisphere is simulated without and with counter-flow injection from the stagnation point and its effect on drag reduction and exergy destruction across the bow shock wave is examined. Initially, wave drag and exergy destruction values are recorded for without jet conditions and then alterations in these parameters are examined when the opposing jet is turned ON for given flow conditions. Results revealed that wave drag reduces while exergy destruction increases with freestream stagnation enthalpy, freestream Mach number and jet pressure ratio. Present study proposes that exergy destruction can be used as an accessing parameter along with drag coefficient to analyze the performance of opposing jet technique.