Scramjet inlets are the most vital component of the engine and their design having more effective on the overall performance of the engine. Thus, the forward capture shape of the engine inlet should conform to the vehicle body shape. A 2-D computational study for scramjet inlet with different ramp length and angles are studied to compress the air by blunted and sharp leading edge, moving the whole cowl up and down, deflecting the cowl lip and axisymmetric inlet with sharp and blunted leading edge. These geometric changes have produced a numerous shocks in inlet and remarkable influence on the flow in several aspects. However, the performance of these inlets tends to degrade as higher Mach number to lower Mach number. These inlets consisting of various ramps producing oblique shocks followed by a cowl shock is chosen in order to increase air mass capture and reduce spillage in scramjet inlets at Mach numbers below the design value. An impinging shock may force the boundary layer to separate from the wall, resulting in total pressure recovery losses and a reduction of the inlet efficiency. Design an inlet to meet the requirements such as Low stagnation pressure loss, High static pressure and temperature gain and deceleration of flow to a desired value of Mach number. Fixed geometry inlets can be used only over a relatively narrow range of Mach number while one method to improve this performance is to use variablegeometry inlets which can be used over a wide range of Mach number with reasonably good pressure recovery. A two dimensional analysis is carried out in this project. CATIA is used to create the model. GAMBIT is used to create the mesh. FLUENT is used to cover the flow analysis.
