This thesis presents the development of a computerized design synthesis for canard-delta combat aircraft. This is complementary to, and follows the philosophy of, an existing RAE system for conventional combat aircraft with swept wings (Ref. 1). The background to the work and the Research Programme objectives and limitations are initially examined. The design of a baseline canard-delta combat aircraft is then described together with all the assumptions and decisions which led to its final configuration. The philosophy behind the progressive evolution of the aircraft geometry and packaging modules from the baseline configuration is explained in detail. The development of detailed modules for the estimation of the aircraft aerodynamics and performance is then presented. A full description of the investigations into the effects of canard-delta interference on the aircraft aerodynamics is also included. The mathematical content of the aircraft geometry, packaging, aerodynamics and performance modules is presented separately in the appendices in greater detail. The development and architecture of the design synthesis and graphics programs are finally presented and the program operation is described with the aid of flow-charts. A comprehensive user's manual and a design example are also provided.