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| Short takeoff/vertical landing variant to be used by U.S. Air Force, U.S. Marines and the United Kingdom, equipped with a shaft-driven lift fan propulsion system which enables the aircraft to take off from a short runway or small aircraft carrier and to land vertically. Engine: Pratt & Whitney JSF 119-PW-611 turbofan deflects thrust downward for short takeoff/vertical landing capability. The Air Force and Navy versions use a thrust-vectoring exhaust nozzle. The Marine Corps and Royal Air Force/Navy version has a swivel-duct nozzle; an engine-driven fan behind the cockpit and air-reaction control valves in the wings to provide stability at low speeds. Other major subcontractors are Rolls Royce and BAE.
This aircraft is the first X-35 ever built. It was originally the X-35A and was modified to include the lift-fan engine for testing of the STOVL concept. Among its many test records, this aircraft was the first in history to achieve a short takeoff, level supersonic dash, and vertical landing in a single flight. It is also the first aircraft to fly using a shaft-driven lift-fan propulsion system. The X-35B flight test program was one of the shortest, most effective in history, lasting from 23 June 2001 to 6 August 2001. On July 7, 2006, the production model F-35 was officially named F-35 Lightning II by T. Michael Moseley, Chief of Staff USAF. SPECIFICATIONS: Dimensions: Overall: 16ft 4 7/8in. x 50ft 9 1/16in., 25000lb., 32ft 11 11/16in. (5m x 15.47m, 11339.9kg, 10.05m) Materials: Composite material aircraft skin, alternating steel and titanium spars. Single-engine, single-seat configuration includes lift-fan and steering bars for vertical flight. Wing span: 10.05 m (33 ft 0 in) Length: 15.47 m (50 ft 9 in) Height: approximately 5 m (15 ft 0 in) Weight: approximately 35,000 lb. |
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| Bibliography: Smithsonian National Air and Space Museum |