Fundamental preliminary design considerations involved in integration are considered in terms 1965 and past technology; U S Army's XV-5A lift-fan research vehicle is used as basis of reference; lift-fan mechanical configuration is duscussed; parameters relating lift-fan static lift to power output of turbojet engine in terms of gas horsepower and gas flow output are established showing effects of three higher energy turbojet cycles on parameters; effects of higher energy turbojet gas generator on composite lift-fan propulsion system are also shown; it is found that 1965 technology can reduce propulsion weight of XV-5A by about 34%.
Lift-fan V/STOL propulsion and airframe integration
Aerodynamics Power Plant Installation -- 2 -- AGARDograph
1965
36 pages
Article (Journal)
English
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