page_title: General Dynamics–Grumman F-111B
section_title: Specifications (F-111B pre-production)
hierarchical_section_title: General Dynamics–Grumman F-111B / Specifications (F-111B pre-production)
caption_attribution_description: English: The General Dynamics F-111B, U.S. Navy BuNo 151974, at the NACA Ames Flight Research Center, NAS Moffett Field, California (USA), during full scale wind tunnel flight control tests. In 1970 the aircraft was dismantled at Moffett Field.
context_page_description: The General Dynamics/Grumman F-111B is a long-range carrier-based interceptor aircraft that was planned to be a follow-on to the F-4 Phantom II for the United States Navy.
  The F-111B was developed in the 1960s by General Dynamics in conjunction with Grumman for the U.S. Navy as part of the joint Tactical Fighter Experimental with the United States Air Force to produce a common fighter for the services that could perform a variety of missions. It incorporated innovations such as variable-geometry wings, afterburning turbofan engines, and a long-range radar and missile weapons system.
  Designed in parallel with the F-111 "Aardvark", which was adopted by the Air Force as a strike aircraft, the F-111B suffered development issues and changing Navy requirements for an aircraft with maneuverability for dogfighting. The F-111B was not ordered into production and the F-111B prototypes were used for testing before being retired. The F-111B would be replaced by the smaller and lighter Grumman F-14 Tomcat, which carried over the engines, AWG-9/Phoenix weapons system, and similar swing-wing configuration.
context_section_description: For pre-production aircraft #6 & #7:
  Data from Thomason, Miller, Logan
  General characteristics
  Crew: 2 (pilot and weapons system operator)
  Length: 68 ft 10 in (20.98 m)
  Wingspan: 
  Spread: 70 ft (21.3 m)
  Swept: 33 ft 11 in (10.34 m)
  Height: 15 ft 9 in (4.80 m)
  Wing area: 
  Spread: 655.5 ft² (60.9 m²)
  Swept: 550 ft² (51.1 m²)
  Airfoil: NACA 64-210.68 root, NACA 64-209.80 tip
  Empty weight: 46,100 lb (20,910 kg)
  Loaded weight: 79,000 lb (35,800 kg)
  Max. takeoff weight: 88,000 lb (39,900 kg)
  Powerplant: 2 × Pratt & Whitney TF30-P-3 turbofans
  Dry thrust: 10,750 lbf (47.8 kN)  each
  Thrust with afterburner: 18,500 lbf (82.3 kN) each
  Performance
  Maximum speed: Mach 2.2 (1,450 mph, 2,330 km/h)
  Range: 2,100 mi (1,830 nmi, 3,390 km) ; with 6 AIM-54 missiles and 23,000 lb fuel internal
  Ferry range: 3,200 mi (2,780 nmi, 5,150 km) ; with 2 x 450 gal external tanks
  Service ceiling: 65,000 ft (19,800 m)
  Rate of climb: 21,300 ft/min (108 m/s)
  Wing loading: 
  Spread: 120 lb/ft² (586 kg/m²)
  Swept: 144 lb/ft² (703 kg/m²)
  Thrust/weight: 0.47
  Armament
  Guns: 1× M61 Vulcan 20 mm (0.787 in) Gatling cannon (seldom fitted)
  Hardpoints: 6 underwing pylons for ordnance and external fuel tanks
  Missiles: 6 x AIM-54 Phoenix long range air-air missiles (four under wings, two in weapons bay)
  Avionics
  AN/AWG-9 Pulse-Doppler radar
caption: F-111B, BuNo 151974, at NAS Moffett Field, California during full-scale wind tunnel flight control tests
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