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Description
The Lockheed F-104B and D models were combat-capable, two-place trainer versions used by the USAF. The 20mm cannon was removed from the aircraft to make room for the second cockpit. The two-seat versions also had a much wider vertical stabilizer. Finally, the nose landing gear was relocated to the front of the wheel well and retracted aft instead of forward as on the A model.

Twenty-six F-104Bs were built (S/N 56-3719 to 2724 and 57-1294 to 57-1313) in four production blocks. The prototype F-104B's (S/N 56-3719) first flight was on Jan. 16, 1957. The USAF bought 21 improved versions as F-104Ds (S/N 57-1314 to 57-1334) in three production blocks. The D model is easily distinguished from the B model by the spacer present between the canopies on the D model. In addition, D models starting with S/N 57-1320 were fitted with a refueling probe.

ype Number built/
converted Remarks
XF-104 2 Prototype; lightweight fighter
YF-104A 17 Service test
F-104A 153 First production aircraft
NF-104A 3 (cv) High-altitude trainer; converted F-104A
F-104B 26 Two-seat trainer
F-104C 77 Improved F-104A
F-104D 21 Improved F-104B
F-104E 0 Designation not used
F-104F * MAP aircraft for Germany; modified D
F-104G * MAP and Consortium built
F-104J * Japanese-built G model
F-104S * Super Starfighter; improved G

Notes:
* = 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

SPECIFICATIONS (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
Engine: One General Electric J79-GE-7A of 15,800 lbs. static sea-level thrust with afterburner
Maximum speed: 1,320 mph (Mach 2)
Cruising speed: 575 mph
Range: Approximately 1,250 nautical miles with two 170 gallon tip tanks and two 195 gallon pylon tanks (dropped when empty) using cruise climb profile: 8.5 min. time-to-climb, 26,000 ft. initial, 34,000 ft. final at approximately .85 Mach for 2 hr. 30 min. With no external stores: 720 nm., 1 hr. 26 min., 6 min. time-to-climb 33,000 initial, 37,000 ft. final.
Service ceiling: 57,500 ft.
Span: 21.94 ft.
Length: 54.77 ft.
Height: 13.49 ft.
Tread: 8.79 ft.
Weight: 23,900 lbs. (tip tanks and pylon tanks); 18,100 lbs. gross wt. with no external load.
Crew: Two

Description
The Lockheed F-104B and D models were combat-capable, two-place trainer versions used by the USAF. The 20mm cannon was removed from the aircraft to make room for the second cockpit. The two-seat versions also had a much wider vertical stabilizer. Finally, the nose landing gear was relocated to the front of the wheel well and retracted aft instead of forward as on the A model.

Twenty-six F-104Bs were built (S/N 56-3719 to 2724 and 57-1294 to 57-1313) in four production blocks. The prototype F-104B's (S/N 56-3719) first flight was on Jan. 16, 1957. The USAF bought 21 improved versions as F-104Ds (S/N 57-1314 to 57-1334) in three production blocks. The D model is easily distinguished from the B model by the spacer present between the canopies on the D model. In addition, D models starting with S/N 57-1320 were fitted with a refueling probe.

ype Number built/
converted Remarks
XF-104 2 Prototype; lightweight fighter
YF-104A 17 Service test
F-104A 153 First production aircraft
NF-104A 3 (cv) High-altitude trainer; converted F-104A
F-104B 26 Two-seat trainer
F-104C 77 Improved F-104A
F-104D 21 Improved F-104B
F-104E 0 Designation not used
F-104F * MAP aircraft for Germany; modified D
F-104G * MAP and Consortium built
F-104J * Japanese-built G model
F-104S * Super Starfighter; improved G

Notes:
* = 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

SPECIFICATIONS (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
Engine: One General Electric J79-GE-7A of 15,800 lbs. static sea-level thrust with afterburner
Maximum speed: 1,320 mph (Mach 2)
Cruising speed: 575 mph
Range: Approximately 1,250 nautical miles with two 170 gallon tip tanks and two 195 gallon pylon tanks (dropped when empty) using cruise climb profile: 8.5 min. time-to-climb, 26,000 ft. initial, 34,000 ft. final at approximately .85 Mach for 2 hr. 30 min. With no external stores: 720 nm., 1 hr. 26 min., 6 min. time-to-climb 33,000 initial, 37,000 ft. final.
Service ceiling: 57,500 ft.
Span: 21.94 ft.
Length: 54.77 ft.
Height: 13.49 ft.
Tread: 8.79 ft.
Weight: 23,900 lbs. (tip tanks and pylon tanks); 18,100 lbs. gross wt. with no external load.
Crew: Two