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 2.0Six (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.
|Span||35 ft. 10 in.|
|Length||81 ft. 11 in.|
|Height||18 ft. 4 in.|
|Weight||In excess of 40,000 lbs.|
|Maximum speed||Mach 3+|
|Combat speed||Mach 2.2 at 75,000 ft.|
|Combat radius||Approximately 450 miles|
|Service Ceiling||Approximately 80,000 ft.|