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North American F-107


The F-107A was originally designed as a tactical fighter-bomber version of the F-100, with a recessed weapon bay under the fuselage. However, extensive design changes resulted in its redesignation from F-100B to F-107A before the first prototype flew. Special features included an all-moving vertical fin; a control system which permitted the plane to roll at supersonic speeds; and a system (Variable Area Inlet Duct) which automatically controlled the amount of air fed to the jet engine.
On Sept. 10, 1956, the No. 1 F-107A made its initial flight, attaining Mach 1.03 (The speed of sound, Mach 1, is about 760 mph at sea level). The aircraft first achieved Mach 2 (twice the speed of sound) in tests on Nov. 3, 1956. Three F-107As were built as prototypes and were test flown extensively, but the aircraft did not go into production, the Republic F-105 having been selected as the standard fighter-bomber for the Tactical Air Command. In late 1957, Nos. 1 and 3 were leased to the National Advisory Committee for Aeronautics (NACA) for high-speed flight research.
 
General characteristics
Power plant One Pratt & Whitney YJ75-P-9 turbojet
Thrust 24,504 lb 109 kN
Wingspan 36.6 ft 11.15 m
Length 61.9 ft 18.86 m
Height 19.7 ft 6.00 m
Max. speed 1,294 mph 2,083 km/h
Initial climb rate 665.4 ft/s 12,169 m/min
Ceiling 53,150 ft 16,200 m
Range normal 790 miles 1,270 km
maximum 2,423 miles 3,900 km
Weight empty 22,708 lb 10,300 kg
max.takeoff 41,450 lb 18,800 kg
Armament 4x 20mm cannon; 6x underwing tips and 1x under fuselage pod (108 2.75 in. rockets and up to 4,000 lbs. of bombs)

Jirka Wagner

 

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