F-16 VISTA

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F-16 VISTA
The VISTA/MATV aircraft in formation with the X-31 (middle) and the F/A 18 HARV (top)
Role	Experimental fighter
Manufacturer	General Dynamics (later Lockheed Martin)
Number built	1
Developed from	F-16 Fighting Falcon

The General Dynamics (now Lockheed Martin) F-16 VISTA ("Variable stability In-flight Simulator Test Aircraft")

The F-16 VISTA testbed aircraft incorporated a multi-axis thrust vectoring (MATV) engine nozzle that provides for more active control of the aircraft in a post-stall situation. The resulting aircraft is supermaneuverable, retaining pitch and yaw control at angles of attack beyond which the traditional control surfaces cannot change attitude.^{[citation needed]}

The VISTA program was considered successful, but the thrust vector control (TVC) never made it into production fighter versions.^{[citation needed]}

The program was also notable for the development of Direct Voice Input and the "Virtual HUD", which were both eventually to be incorporated into the cockpit design for the F-35 Lightning II.^[1] The STOVL F-35 variants also incorporate MATV while hovering to provide attitude control.^{[citation needed]}

Contents 1 Specifications 2 See also 3 References 4 External links

Specifications

The F-16 VISTA is a Block 30 F-16D based on the airframe design of the Israel Air Force version, which incorporates a dorsal fairing running the length of the fuselage aft of the canopy and a heavyweight landing gear derived from the Block 40 F-16C/D. The fairing houses most of the variable-stability equipment and test instrumentation. The heavyweight gear will permit simulation of aircraft with higher landing sink rates than a standard F-16.

This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.

Data from USAF sheet,^[2] AerospaceWeb^[3]

General characteristics

• Crew: 2 (one test pilot and one safety pilot)^[4]
• Length: 49 ft 5 in (14.8 m)
• Wingspan: 32 ft 8 in (9.8 m)
• Height: 16 ft (4.8 m)
• Wing area: 300 ft² (27.87 m²)
• Airfoil: NACA 64A204 root and tip
• Empty weight: 18,238 lb (8,272 kg)
• Loaded weight: 26,463 lb (12,003 kg)
• Max takeoff weight: 42,300 lb (16,875 kg)
• Powerplant: 1× General Electric F110 afterburning turbofan
  • Dry thrust: 14,590 lbf (64.9 kN)
  • Thrust with afterburner: 23,770 lbf (105.7 kN)

Performance

• Maximum speed:
  
  • At sea level: Mach 1.2 (915 mph, 1,460 km/h)
  • At altitude: Mach 2+ (1,500 mph, 2,414 km/h)
• Ferry range: >3,200 mi (2,800 NM, 4,800 km)
• Service ceiling: >50,000 ft (15,239 m)
• Rate of climb: 50,000 ft/min (254 m/s)
• Wing loading: 88.2 lb/ft² (431 kg/m²)
• Thrust/weight: 1.095

See also

Wikimedia Commons has media related to: F-16 Fighting Falcon

Related development

• F-16 Fighting Falcon
• General Dynamics F-16XL
  

Comparable aircraft

• Rockwell-MBB X-31
  

References

External links

• F-16XL number 1 photo gallery
• F-16XL number 2 photo gallery
• NASA report
• NASA Could Put The F-16XL Back In The Air (2007)
• Harry Hillaker — Father of the F-16

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