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The NASA sponsored studies of the potential of the turbofan engine for light aircraft have approached the total aircraft design and mission rather than the engine cycle and design alone. In addition, the commonality of military trainer and civil requirements have been addressed. It has been demonstrated that the proper choice of turbofan engines coupled with advanced wing and flap design will result in either a superior or comparable aircraft design for all classes of light aircraft. Improved noise and emission characteristics can be expected with comparable fuel consumption. Costs are a question mark, but high volume production techniques could result in marked reductions in turbofan engine costs.

Circulation control wing (CCW) technology has been in the research and development phase for over sixty years with a minimal amount of practical applications to subsonic transport aircraft. The concept is based on the use of high pressure Coanda jet air that is diverted from the fan or compressor of the main turbofan engines; however, this can create a significant decrease in engine performance. This paper will provide the background of past CCW research and conclude with recommendations for a conceptual design for a circulation control wing that implements multiple, lightweight gas generators, which are separate from the main aircraft engines that provide high pressure air or exhaust gas to the wing leading and trailing.