Scramjets are air-breathing engines used in the propulsion of hypersonic vehicles. The design of scramjets mainly depend on the design of their intakes. Out of the various intake types, mixed compression intakes are commonly used because of their inherent advantages over other intakes. This paper discusses the design of a two-ramp variable area mixed compression intake with a free-stream Mach number of 6.5. Shock-on-lip condition required to obtain maximum capture of air entering the intake is satisfied in the design procedure. A detailed analysis of the performance of the intake due to variation of the flight conditions in terms of the free-stream Mach number, angle of attack and cowl deflection is carried out using inviscid numerical simulations.