Abstract: Combat aircraft are designed to operate over a wide range of flow conditions. The requirements due to speed, maneuverability and stealth has a major impact on air intake design. The air intake should be able to give good quality flow to the engines over the entire flight envelope of the aircraft. Supersonic fighter aircrafts employ various mechanisms such as boundary layer bleed, variable intake geometry, etc to have stable operation and good efficiency throughout the flight envelope. These additions lead to an increase in weight and complexity of the intake design and adversely affect the stealth characteristics of the aircraft. There has been a growing interest in Diverterless Supersonic Intakes for supersonic fighter aircraft due to its ability to divert boundary layer air and at the same time give efficient supersonic compression without the disadvantages associated with offset intakes. A fifth generation fighter aircraft has been integrated with a diverterless supersonic intake and evaluated across the flight envelope using RANS solver. Geometric parametrization of duct shape is attempted using class shape transformation. Future plans include optimization of the duct shape using genetic algorithms.