General technical data

AIRCRAFT

Length

54 ft. 8 in.

(16.66 m.) (without pitot boom)

Wingspan

22 ft. 0 in.

(6.70 m.)

Height

13 ft. 6 in.

(4.12 m.)

Empty weight

13,865 lbs.

(6,267 Kg.)

Loaded weight

20,900 lbs.

(9,446 Kg.)

Operational weight

26,625 lbs.

(12,034 Kg.) ( with maximum fuel)

Max. T.O. weight

29,027 lbs.

(13,170 Kg.)

Max. speed

1,323 Kts.

(2,447 Km/h.)

Combat radius

365 NM.

(675 Km.)

Ferry range

1,420 NM.

(2,627 Km.)

Service ceiling

50,000 ft.

(15,000 m.)

Rate of climb

48,000 ft/min.

(244 m/sec.)

Wing load

105 lbs/ft²

(514 Kg/m².)

Thrust/weight ratio

0.54 with max. T.O. weight.

Lift/drag ratio

9.2

Zero lift-drag coëfficient

0.0172

Drag area

3.37 ft².

(0,31 m².)

Aspect ratio

2.45

Internal fuel capacity

5,746 lbs.

(2,610 Kg.)

Tip tank fuel capacity

2,210 lbs.

(1,002 Kg.)

Pylon tank fuel capacity

2,534 lbs.

(1,148 Kg.)

WINGS

Wing area

196.1 ft².

(18.22 m².)

Airfoil

bi-convex  3.36%  (root and tip)

Root chord

155.5 in.

(3.95 m.)

Tip chord

58.66 in.

(1.49 m.)

Mean Aerodynamic Chord

114.56 in.

(2.91 m.)

AILERONS

Aileron area

9.47 ft².

(0.88 m².) totally

Deflection

15° up and down

TRAILING EDGE FLAPS

Trailing edge flap area

23.13 ft².

(2.15 m².) totally

Deflection

45° down max.

LEADING EGDE FLAPS

Leading edge flap area

17 ft².

(1.58 m².) totally

Deflection

30° down max.

HORIZONTAL STABILIZER

Horizontal stabilizer area

48.21 ft².

(4.48 m²)

Deflection

17° down and 5° up (at leading edge)

Airfoil

bi-convex

Root chord

77.16 in.

(1.96 m.)

Tip chord

37.40 in.

(0.96 m.)

Mean aerodynamic chord

55.12 in.

(1.40 m.)

VERTICAL STABILIZER

Vertical stabilizer area

47.77 ft².

(4.44 m².)

Rudder area

5.48 ft².

(0.51 m².)

Rudder deflection

20° left and right

Airfoil

bi-convex

Root chord

138.58 in.

(3.52 m. at WL 138)

Tip chord

51.97 in.

(1.32 m. at WL 203.5)

Mean aerodynamic chord

106.7 in.

(2.71 m. at WL 162.6)

SPEED BRAKES

Speed brake projected area

8.28 ft²

(0.77 m².) totally

Maximum extention

60°

VENTRAL FIN

Ventral fin area

5.81 ft²

(0.54 m².)

POWER PLANT

Power plant

1 General Electric J-79 GE11A afterburning turbojet

Basic weight

3,560 lbs.

Overall length

207.96 in. (cold)

209.46 in. (hot)

Max. envelope diameter

35.18 in. (cold)

35.48 in. (hot)

Compressor

17 stage (first 6 guide vanes variable)

Turbine

3 stage

Engine Pressure Ratio

12/1

Primary airflow

160 lbs/sec.

Secondary airflow

10 lbs/sec.

Idle RPM

5.000

Thrust 500 lbs.

EGT 120-420 °C.

Normal RPM

7.460

Thrust 9,700 lbs.

EGT 560 °C.

Military RPM

7.460

Thrust 10,000 lbs.

EGT 590 °C.

Minimum  A/B RPM

7.460

Thrust 12,320 lbs.

EGT 590 °C.

Maximum A/B RPM

7.460

Thrust 15,800 lbs.

EGT 590 °C.

Fuel consumption

1.97 lbs/sec. (at maximum A/B)

FIXED ARMAMENT

Fixed armament

1 General Electric M61A1 Vulcan gun (F-104G only)

Gun barrel

6 (progressive RH parabolic twist / 9 grooves)

Weight

248 lbs.

(112 Kg. ) (excl. Ammo feed system)

Length

73.8 in.

(1.88 m.)

Caliber

0.787 in.

(20 mm.)

Cartridge

0.787 x 4.01 in.

(20 mm. X 102 mm.)

Action drive

Electric

Firing ignition

Electric

Firing rate

4,200 rounds/min.

70 rounds/sec.)

Muzzle velocity

3,450 ft/sec.

(1,050 m/sec.)

(with PGU-28 Semi Armor Piercing High Explosive Incendiary Round)