Solid oxide fuel cell (SOFC) is the most promising candidate for utilization of waste generated from the GT based power system. By coupling SOFC with gas turbine (GT) based power system, a hybrid SOFC–GT power system has been developed and the thermal efficiency of the system can be enhanced upto 70-85%. This paper focuses of thermodynamic analysis of an internal reformed solid oxide fuel cell which is integrated with the gas turbine cycle to form a hybrid power generation system for an unmanned aerial vehicle (UAV) with a long range. Thermodynamic 1st and 2nd law, parametric analysis has been carried out and the effect of various parameters such as compressor pressure ratio, turbine inlet temperature, air flow rate has been examined. In order to validate the results, present work has been compared with the available literature and it shows good agreement. The results obtained from energy and exergy analysis are employed to evaluate the thermodynamic losses in each cycle component and to estimate the work potentials of the fluid streams as well as heat interactions. It has been observed that by increasing TIT, the performance of hybrid cycle can be increased significantly. Moreover, on increasing the air flow rate the exergy destruction within SOFC decreases linearly while in the combustor exergy destruction increases linearly. The proposed system has immense potential when applied to aerospace application.