Curtiss XF14C: Difference between revisions
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<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. -->{{Infobox Aircraft |
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|name = XF14C |
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|type = Carrier fighter |
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|manufacturer = [[Curtiss-Wright Corporation|Curtiss]] |
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|image = |
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|caption = |
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|designer = |
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|first flight = July [[1944 in aviation|1944]] |
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|introduced = |
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|retired = |
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|status = Cancelled |
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|primary user = [[United States Navy|US Navy]] |
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|more users = |
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|produced = |
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|number built = 1 |
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|variants with their own articles = |
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The '''Curtiss XF14C''' was an airplane developed by the [[Curtiss-Wright Corporation]] in response to a request by the [[U.S. Navy]] in 1941 to produce a new shipboard high-performance [[fighter aircraft]] powered by the [[Lycoming XH-2470]] [[liquid-cooled engine]]. On [[June 30]] [[1941]] a contract for two [[prototype]] aircraft, designated the '''XF14C-1''', was awarded. On the same date prototype development contracts were also awarded to [[Grumman Aircraft Engineering Corporation]] for the single engine [[XF6F-1]] and the twin engine [[XF7F-1]]. |
The '''Curtiss XF14C''' was an airplane developed by the [[Curtiss-Wright Corporation]] in response to a request by the [[U.S. Navy]] in 1941 to produce a new shipboard high-performance [[fighter aircraft]] powered by the [[Lycoming XH-2470]] [[liquid-cooled engine]]. On [[June 30]] [[1941]] a contract for two [[prototype]] aircraft, designated the '''XF14C-1''', was awarded. On the same date prototype development contracts were also awarded to [[Grumman Aircraft Engineering Corporation]] for the single engine [[XF6F-1]] and the twin engine [[XF7F-1]]. |
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==Specifications (XF14C-2)== |
==Specifications (XF14C-2)== |
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{{aircraft specifications |
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|plane or copter?=plane |
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===General characteristics=== |
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|jet or prop?=prop |
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|ref= |
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* '''Length:''' 37 ft 9 in (11.5 m) |
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* '''Wingspan:''' 46 ft (14.0 m) |
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|capacity= |
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* '''Height:''' 12 ft 4 in (3.8 m) |
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|payload main= |
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* '''Wing area:''' 375 ft² (35 m²) |
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|payload alt= |
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* '''Empty:''' 10,582 lb (4800 kg) |
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|length main= 37 ft 9 in |
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* '''Loaded:''' 13,405 lb (6080 kg) |
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|length alt= 11.5 m |
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* '''Maximum takeoff:''' 14,582 lb (6614 kg) |
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|span main= 46 ft |
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|span alt= 14.0 m |
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|height main= 12 ft 4 in |
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===Performance=== |
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|height alt= 3.8 m |
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|area main= 375 ft² |
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|area alt= 35 m² |
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* '''Service ceiling:''' 39,500 ft (12,000 m) |
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|airfoil= |
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* '''Initial rate of climb:''' 2,700 ft/min (820 m/min) |
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|empty weight main= 10,582 lb |
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|empty weight alt= 4800 kg |
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* '''Wing loading:''' kg/m² ( lb/ft²) |
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|loaded weight main= 13,405 lb |
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* '''Power/mass:''' 2,300 hp |
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|loaded weight alt= 6080 kg |
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--> |
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|useful load main= |
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|useful load alt= |
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===Armament (Planned)=== |
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|max takeoff weight main= 14,582 lb |
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|max takeoff weight alt= 6614 kg |
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|more general= |
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|type of prop= |
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|number of props=1 |
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|power main= 2,300 hp |
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|power alt= 1.7 MW |
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|power original= |
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|max speed alt= 510 km/h at sea level, 682 km/h at 9,800 m |
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|cruise speed main= |
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|cruise speed alt= |
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|stall speed main= |
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|stall speed alt= |
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|never exceed speed main= |
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|never exceed speed alt= |
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|range alt= 2181 km at 260 km/h |
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|ceiling main= 39,500 ft |
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|ceiling alt= 12,000 m |
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|climb rate main= 2,700 ft/min |
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|climb rate alt= 820 m/min |
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|loading main= |
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|loading alt= |
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|thrust/weight= |
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|power/mass main= |
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|more performance= |
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|armament= |
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|avionics= |
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}} |
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==References== |
==References== |
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Revision as of 02:07, 19 March 2007
Template:Infobox Aircraft The Curtiss XF14C was an airplane developed by the Curtiss-Wright Corporation in response to a request by the U.S. Navy in 1941 to produce a new shipboard high-performance fighter aircraft powered by the Lycoming XH-2470 liquid-cooled engine. On June 30 1941 a contract for two prototype aircraft, designated the XF14C-1, was awarded. On the same date prototype development contracts were also awarded to Grumman Aircraft Engineering Corporation for the single engine XF6F-1 and the twin engine XF7F-1.
Early in the development the Navy requested better altitude performance and, in view of unsatisfactory progress in the development of the XH-2470 engine, Curtiss adapted the design of the aircraft around the new turbocharged Wright R-3350 Duplex-Cyclone engine. The aircraft equipped with this eighteen cylinder twin row radial air-cooled engine and three bladed contra-rotating propellers was designated the XF14C-2. The XF14C-1 was canceled. Also, looking at the problems of operation at altitudes of about 40,000 feet (12,000 m), the Navy also initiated work on a third version with a pressurized cockpit designated the XF14C-3.
Ultimately, only the XF14C-2 prototype was completed, flying for the first time in July 1944. Moreover, disappointment with performance estimates and delays with the availability of the XR-3350-16 engine coupled with the tactical need for an extremely high altitude fighter that failed to materialize led to cancellation of the development.
Specifications (XF14C-2)
General characteristics
- Crew: one, pilot
Performance
Armament
- 4 × wing mounted 20 mm cannon (planned)
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This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |
References
- William Green (1961). War Planes of the Second World War - Fighters, (Vol 4). London: MacDonald
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