The design of a vertical or short takeoff and landing airplane powered by jet or turbofan lift engines is primarily an exercise in propulsion package and airframe matching. This task is complicated by the unique requirements and constraints imposed by the takeoff and landing profiles of hybrid jet-lift airplanes. Performance of such aircraft is sensitive to the overall propulsion system capabilities, specifically to thrust vector management, lift-engine bypass ratios, airframe-engine interactions and power plant packaging. In turn, the complete propulsion system design is related to the airplane wing loading and aerodynamic high-lift system. This paper examines the propulsion system/airframe matching considerations that influence the V/STOL vehicle propulsion system design, as seen from the preliminary design engineer’s point of view.

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