Design of a Highly Compact Supersonic Cruise Missile (SSCM) Inlet

The objective of the proposed effort is to demonstrate the feasibility of designing a Mach 2.5 inlet for a high-speed cruise missile. This inlet must provide the proper airflow to a turbojet engine for flight Mach numbers from 0.4 to 2.5. It must be light weight, be compact, have low cost and simple or fixed geometry, and meet the constraints of being packaged within a vehicle very similar to the current subsonic Tomahawk cruise missile. The proposed inlet design feasibility study would result in the identification of a several possible inlet concepts, and identify the relative benefits and shortcomings of each (complexity, cost, weight, performance, volume, operability, etc.), and provide a recommendation for the most promising inlet design for continued development.