الأقســـام العسكريـــة

F-102 Delta Dagger

The Convair F-102 Delta Dagger was a US interceptor aircraft built as part of the backbone of the United States Air Force's air defenses in the late 1950s. Entering service in 1956, its main purpose was to intercept invading Soviet bomber fleets.
The F-102 was the first operational supersonic interceptor and delta-wing fighter of the USAF. It used an internal weapons bay to carry both guided missiles and rockets. As originally designed, it could not achieve Mach 1 supersonic flight until redesigned with area ruling. The F-102 replaced subsonic types such as the Northrop F-89 Scorpion, and by the 1960s, it saw limited service in Vietnam in bomber escort and ground attack roles. It was supplemented by McDonnell F-101 Voodoos and, later, by McDonnell Douglas F-4 Phantom IIs. Many of the F-102s were transferred to United States Air National Guard duty by the mid-to-late 1960s, and the type was retired from operational service in 1976. The follow-on replacement was the Mach 2 class Convair F-106 Delta Dart which was an extensive redesign of the F-102.

Variants

YF-102
Prototypes. Non area-ruled fuselage. Powered by 14,500 lbf (64.5 kN) J57-P-11, two built.
YF-102A
Area-ruled prototypes. 16,000 lbf (71.2 kN) J57-P-23. Four converted from pre-production aircraft.
F-102A
Production Model. Initial eight pre-production aircraft built with non-area ruled fuselage. Remainder (879) with area ruled fuselage.
TF-102A
Two-seat training version, 111 built
F-102B
The original designation of the F-106A
F-102C
Proposed tactical attack version with J57-P-47 engine. Two converted As as YF-102C engineering test beds.[19]
QF-102A
Target drones converted from the F-102A. Six built.[20]
PQM-102A
Unpiloted target drones. 65 converted.[20]
PQM-102B
Revised target drone conversion, capable of being flown remotely or by pilot in cockpit. 146 converted.[20]

General characteristics
Crew: 1
Length: 68 ft 4 in (20.83 m)
Wingspan: 38 ft 1 in (11.61 m)
Height: 21 ft 2 in (6.45 m)
Wing area: 661.5ft²/61.52m² (Original Wing) or 695 ft²/64.57m² (Conically-Cambered Wing) ()
Airfoil: NACA 0004-65 mod root and tip
Empty weight: 19,350 lb (8,777 kg)
Loaded weight: 24,500 lb (11,100 kg)
Max takeoff weight: 31,500 lb (14,300 kg)
Powerplant: 1× Pratt & Whitney J57-P-25 afterburning turbojet
Dry thrust: 11,700 lbf (52.0 kN)
Thrust with afterburner: 17,200 lbf (76.5 kN)
Internal fuel capacity: 1,085 US gal (4,107 l)
External fuel capacity: 2 × 215 US gal (815 l) drop tanks
Performance
Maximum speed: Mach 1.25 (825 mph, 1,304 km/h) at 40,000 ft (12,190 m)
Range: 1,350 mi (1,170 nmo, 2,175 km)
Service ceiling: 53,400 ft (16,300 m)
Rate of climb: 13,000 ft/min (66 m/s)
Wing loading: 35 lb/ft² (172 kg/m²)
Thrust/weight: 0.70
Armament
Rockets: 24 × 2.75 in (70 mm) FFAR (Folding Fin Aerial Rocket) unguided rockets in missile bay doors
Missiles:
6 × AIM-4 Falcon air-to-air missiles or
3 × AIM-4 Falcon
1 × AIM-26 Falcon with conventional or nuclear warhead
Avionics
MG-10 fire control system