This paper examines the influence of some of the key performance characteristics of typical future STOL transport aircraft on the requirements of the propulsion system. Airplane characteristics such as takeoff field length, cruise altitude, cruise speed and range are examined to see how they influence the choice of engine cycle. The effect of engine design variables such as overall pressure ratio, bypass ratio for turbofans and turbine temperature are discussed. Potential trade-offs of engine thrust to weight ratio, performance, and cost are reviewed. Propulsion system installation and integration problems peculiar to the STOL transport are also discussed.