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| D-188A |
(XF-109 / XF3L)
||Status||Primary users|| Number built
The Bell D-188A (unofficial military designations XF-109/XF3L) was a proposed eight-engine Mach 2-capable vertical take-off and landing (VTOL) tiltjet fighter that never proceeded past the mock-up stage.
In 1955, Bell Aircraft was requested by both the USAF and the US Navy to develop a VTOL/STOVL supersonic, all-weather fighter-bomber and defence interceptor. The project was highly ambitious and was designed to fulfill a multitude of roles for two different services. The aircraft was designated the Model 2000, and was offered in two different versions – the D-188 for the Navy and the D-188A for the Air Force. Bell had rather optimistically called the Navy version the XF3L-1 and the Air Force version the XF-109, although neither of these designations were official. On 5 December 1960, Bell publicly showed off the design as the XF-109 – the Air Force version, as the Navy had lost interest the year earlier, however in the spring of 1961, the US Air Force canceled the program and no examples were built.
The military designations were not official and were speculative on the part of Bell. The Navy’s XF3L-1 was not assigned, but would have been the D-188’s designation had the aircraft been built, as this was the next in the US Navy's number series. The Air Force XF-109 designation had previously been assigned to a proposed Convair F-106B variant, however, had subsequently been left blank and Bell assumed – if the D-188A had been built – that this would have been assigned to the aircraft. Many reference works refer to the D-188A by its assumed experimental series number, but in fact the XF-109 designator was never assigned.
The aircraft was unconventional, and consisted of a long, thin, area ruled fuselage with a large fin and all-moving stabilators in the tail. The single seat cockpit was in the extreme nose and the small-span wing was mounted high on the fuselage. At the ends of each wing were pods that contained two turbojets each. These pods were designed to swivel through an arc of 100° (horizontal to 10° past vertical) to allow for both horizontal and vertical flight. To take off vertically, the pods were rotated to direct the engine's thrust downward, while for horizontal flight the pods were rotated back to the horizontal. The pods were capable of directing thrust slightly forward as well for enhanced landing maneuvers. In addition to the four wing engines, four engines were also mounted in the fuselage – two in the rear directed out of two separate tail ducts, and two directly aft of the cockpit and positioned vertically to aid in VTOL operation, exhausting out of two ventral ducts. The D-188A featured an engine bleed system to assist in vertical lift and maneuvering. Bleed air from the fuselage engine compressors would have been directed to a pair of thrusters in the nose and two more in the tail to aid in pitch, roll and yaw movements.
Armament would have consisted of two 20mm cannon in the fuselage, an internal weapons bay and eight wing hard points for missiles and other ordnance.
Specifications (D-188A, as designed)
Data from General characteristics
- Crew: 1
- Length: 62 ft (18.90 m)
- Wingspan: 23 ft 9 in (7.24 m)
- Height: 12 ft 9 in (3.89 m)
- Wing area: 194 ft² (18.02 m²)
- Empty weight: 13,800 lb (6,260 kg)
- Loaded weight: 23,917 lb (10,849 kg)
- Powerplant: 8 × General Electric J85-GE-5 turbojets, 2,600 lbf (11.6 kN) each
- Maximum speed: Mach 2.3
- Range: 2,000 nmi (2,300 mi, 3,900 km)
- Combat radius: 1,350 mi ()
- Service ceiling: 60,000 ft (18,000 m)
- Thrust/weight: 0.87</ul>Armament
- Aircraft of comparable role, configuration and era
- Related lists
- Jenkins, Dennis R. and Tony R. Landis. Experimental & Prototype U.S. Air Force Jet Fighters. Minnesota, US: Specialty Press, 2008. ISBN 978-1-58007-111-6.
- Townend, David R. Clipped Wings – The History of Aborted Aircraft Projects, Markham, Ontario, AeroFile Publications, 2007, ISBN 978-0-9732020-4-5.
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