Airplane description from T.O. 1F-104G-1 - The single-place F-104G and two-place TF-104G airplanes are high-performance, all-weather, day and night fighter-bomber-interceptors powered by an axial-flow, turbojet engine with afterburner. The airplane, built by the Lockheed Aircraft Corporation, is designed for high subsonic cruise and high supersonic combat speeds. The two-place TF-104G is used primarily as a pilot trainer. Notable features of the airplane include extremely thin flight surfaces, short straight wings with negative dihedral, irreversible-hydraulically-powered flight controls, controllable horizontal stabilizer, engine inlet duct anti-icing, an antiskid brake system, an automatic pitch control system, and on single-place aircraft a maneuvering automatic pilot. The wings have leading edge and trailing edge flaps, and a boundary layer control system which is used in conjunction with the trailing edge flaps to reduce landing speeds. An upward ejection system is used for emergency escape. A drag chute is installed to reduce the landing roll and an arresting hook is available for bringing the aircraft to an emergency stop. Internal fuel cells and external fuel tanks may be serviced through a single-point pressure refueling system. The photo reconnaissance version of the F-104G has three cameras installed in area of the shellcase stowage compartment and is referred to as the RF-104G.
The F-104G was an improved version of the C model built in the US under the Military Assistance Program and internationally by Consortium. The USAF never bought any G models; however, the aircraft was operated by the USAF for training of non-USAF pilots primarily from Germany.
Prototype; lightweight fighter
First production aircraft
High-altitude trainer; converted F-104A
Designation not used
MAP aircraft for Germany; modified D
MAP and Consortium built
Japanese-built G model
Super Starfighter; improved G
* = not procured by USAF
MAP = Military Assistance Program; U.S. built for other countries
Consortium = built by using (non-U.S.) country
22 F-104As were converted to QF-104 target drones
TECHNICAL NOTES (F-104A from T.O. 1F-104A-1): Armament: Basic armament consists of two AIM-9B air-to-air guided missiles, carried one on each wing tip in place of the tip tanks; aircraft also incorporates a M61 20mm electrically operated gun located on the lower left side of the forward fuselage; its ammunition supply of 725 rounds is fired at an average rate of 4,000 rounds per minute; up to 5,800 lbs. of external stores including tip or pylon fuel tanks, sidewinder missiles and bombs Engine: One General Electric J79-GE-11A (or -11B) turbojet of 15,800 lbs. static sea-level thrust with afterburner Maximum speed: 1,320 mph (Mach 2) Cruising speed: 575 mph Range: 1,628 nautical miles maximum Service ceiling: 60,000 ft. Span: 21.94 ft. Length: 54.77 ft. Height: 13.49 ft. Tread: 8.79 ft. Weight: 20,800 lbs. gross takeoff weight with no external load (includes full internal fuel, 725 rounds of ammunition and pilot). TF-104G: 19,350 lbs. gross takeoff weight Crew: One (two in the TF-104G)