| 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) |
|
|
|
