A computer-aided design procedure is described for use in conceptual design for sizing and shaping supersonic non-circular missiles with turbojet or ramjet propulsion systems. The theoretical basis for the method, which uses a sensitivity derivative approach, is developed. Avionics, structures, payload, inlet, engine, fuel, aerodynamic and performance models are described. Inlet/engine sizing, external moldline shaping and interactive graphics design processes are presented. The synthesis procedure overcomes many of the major drawbacks of airbreathing missile synthesis. It has features such as: simple initial geometry setup for body, wings, tails and inlets; modeling of completely arbitrary missile shapes; non-circular subsystem packaging; non-circular and multiple inlet modeling; aerodynamic and performance shaping; low cost, short duration computer sessions; rapid convergence; and accurate aerodynamic predictions. Two example configuration shapings are provided to depict the sizing process.


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