A two-dimensional unstructured finite volume Euler solution developed in-house is used to simulate supersonic intake difficulties. Data from the commercial program ANSYS Fluent has been used to verify the findings of the current solver. The inviscid flux is calculated using Van Leer’s flux vector splitting technique. The current solver’s and Fluent’s findings compare well. Both Mach numbers 2 and 2.2 are used while operating the intakes. The intake should commence under Mach number 2.2, which is the on-design condition. Here, in this investigation, the authors are interested in initiating the intake at Mach 2. Research has been done by significantly altering the intake design to start the inlet at an off-design Mach number (i.e., Mach number 2). This may be done by using the bleed in intake in conjunction with the cowl deflection, or by using the cowl deflection by itself.