Aircraft intake plays a vital role in overall performance of the aircraft. Purpose of intake is to supply less turbulent and smooth flow to the engine. It must provide maximum pressure recovery for a wide range of operating conditions. Conventional ramp intakes have been used in many older and few modern fighter aircraft (F4 Phantom II, Mig 21, Mig 27, Mirage 2000 & F-14 Tomcat). However, DSI (Diverter Less Supersonic Intake) were used in modern aircraft (JF -17 Block 3, F- 35 & J -20). Weight, complexity & maintenance cost can be reduced using DSI compared in comparison to the conventional intake. Furthermore, DSI provides higher pressure recovery, lesser boundary layer & less complex geometry. The aim of this research is to model different bump configurations and carry out their CFD analysis in order to establish high performing configuration of DSI air intakes at subsonic & supersonic regimes. Four bump configurations named as smaller, softer, blunter and original bump were modelled in ANSYS at three different speed regimes (Mach No 0.6, 0.95 & 1.5) & comparison was drawn for each type of DSI bump configuration & it was found that pressure recovery of DSI of all four configuration is approximately same in subsonic regions whereas for transonic regime (Mach 0.95) DSI smaller has highest pressure recovery value of 0.868 & supersonic regime bump original has highest pressure recovery value of 0.779. This shows that smaller & smoother bump intake configuration will provide maximum pressure recovery and its position into the air intake is crucial for the pressure recovery.
