Conceptual design has critical leverage on the entire course of design process since it addresses the issue of selecting the baseline design to optimally accomplish the specified set of requirements. Conceptual design software has been developed to determine the optimal engineairframe match over a given mission role, its multi-mission capabilities, and the size and weight of optimum engine cycle. Its capabilities are demonstrated over three combat mission applications. The results are presented to indicate the optimum designs over these missions, interaction effects of a few design variables and the future course of developments in propulsion system technology. The results also include a preliminary estimate of the impact of thrust vectored take off and landing and a variable capacity low pressure turbine on engine cycle selection and overall aircraft sizing.
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