Responder al tema

Mensaje: <blockquote data-quote="Grulla" data-source="post: 565336" data-attributes="member: 5064">Y los de Republic no se andaban con vueltas en esa epoca, imagina si este era "un poco mas lento" que el XF-103 que era de los 50Republic XF-103 The XF-103 was developed as a high-speed high-altitude aircraft specifically designed to intercept incoming enemy bombers. The XF-103 was proposed in the same contract competition that resulted in the Convair F-102--Project MX-1554 Interceptor Fighter Airplane. The Republic design, Model AP-57, underwent a design performance evaluation conducted by the Air Material Command (AMC). The results showed an estimated top speed of 1438 knots. A limiting Mach number of 3.0 was quoted due to excessive (estimated) turbine inlet air temperature. The Republic XF-103 Model AP-57 had a Delta wing swept-back 55 degrees at the leading edge and incorporates a variable incidence feature. The horizontal tail is of the Delta configuration with a sweep-back angle of 60 degrees at the leading edge. The alighting gear was of the tricycle type and retracts into the fuselage. The turbo-jet was a Wright Aeronautical Corporation XJ-67-W-1 power plant with afterburner. A Ferri type two-dimensional engine air inlet is used. The thrust of the turbo-jet engine was limited at high Mach numbers by the allowable turbine inlet temperature. The air bypassed the engine compressor and turbine, and using the afterburner as a ram-jet combustion chamber, the available thrust is greatly increased above a Mach number of 2.0 Six (6) MX-904 missiles and 36 2.75 in. FFA rockets internally stowed were proposed. The missile launching system was complex with six (6) individual tracks and actuating cylinders. Accessibility of all launchers for loading was adequate, though rockets and especially missiles were poorly located in the immediate area of the engine air scoop. Most of the Electronic and Control system were located in a compartment adjacent to the radar equipment. Fuel was contained in five pressurized fuel cells. No self-sealing or armor was proposed for the fuel system. The USAF canceled the XF-103 development contract on 21 August, 1957 when the aircraft was in the mock-up phase. Specifications (XF-103, as designed)XF-103 mock-upGeneral characteristicsCrew: one pilot Length: 77 ft (23.5 m) Wingspan: 34 ft 5 in (10.5 m) Height: 16 ft 7 in (5.1 m) Wing area: 401 ft² (37.2 m²) Empty weight: 24,949 lb (11,317 kg) Loaded weight: 38,505 lb (17,466 kg) Max takeoff weight: 42,864 lb (19,443 kg) Powerplant: 1× Wright XJ67-W-3 turbojet, 15,000 lbf (66.7 kN) 1× Wright XRJ55-W-1 ramjet, 18,800 lbf (83.6 kN) PerformanceMaximum speed: Mach 3 (as a turbojet) / Mach 5 (ramjet-only) Service ceiling 80,000 ft + (24,390 m +) Rate of climb: 19,000 ft/min (5,800 m/min) Wing loading: 96 lb/ft² (470 kg/m²) Thrust/weight (jet): 0.57:1 (afterburner only); 0.95:1 (afterburner and ramjet) Combat radius: 245 mi (394 km) Ferry range: 1,545 mi (2,486 km) Armament36 × 2.75-in (70 mm) FFAR rockets and 6 × GAR-1/GAR-3 AIM-4 Falcon or 4 × GAR-1/GAR-3 AIM-4 Falcon missiles + 2 × Nuclear-Tipped air-to-air missiles<img src="http://img230.imageshack.us/img230/8574/f1032jm0.jpg" alt="" class="fr-fic fr-dii fr-draggable " style="" /></blockquote>

Verificación: Guerra desarrollada entre Argentina y el Reino Unido en 1982