Steven F. Udvar-Hazy Center: Lockheed Martin X-35B Joint Strike Fighter (Pratt & Whitney JSF 119-PW-611 engine displayed next to the plane, with redirectable thruster nozzles for vertical takeoff & landing)
Quoting from the X-35B STOVL Propulsion System museum caption:
Lockheed Martin conceived a unique propulsion system to achieve short-takeoff and verticcal landing (STOVL) flight for the X-35B Joint Strike Fighter. At the system's center is the Pratt & Whitney JSF 119-PW-611 turbofan engine that powered both conventional and STOVL versions of the X-35. Rolls-Royce developed the STOVL components. A vertical shaft-driven lift fan and a three-bearing swivel-duct nozzle created downward thrust, while roll control ducts provided stability at low speeds.
This integrated system enabled the X-35B to make the world's first short takeoff, level supersonic dash, and vertical landing in a single flight on July 20, 2001. The partners in its development, which also included Northrop Grumman, BAE Systems, and the Joint Strike Fighter Program Office, received the prestigious Collier Trophy for 2001 from the National Aeronautics Association.
Transferred from the Department of Defense Joint Strike Fighter Program Office
Major support for the display of the X-35B STOVL Propulsion System provided by Pratt & Whitney
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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 June 23, 2001 to August 6, 2001.
The lift-fan propulsion system is now displayed next to the X-35B at the Steven F. Udvar-Hazy Center near Dulles Airport.
On July 7, 2006, the production model F-35 was officially named F-35 Lightning II by T. Michael Moseley, Chief of Staff USAF.
Transferred from the United States Air Force.
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.
Composite material aircraft skin, alternating steel and titanium spars. Single-engine, single-seat configuration includes lift-fan and steering bars for vertical flight.
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.