The Saturn (Model 75) was a small feeder airliner produced by Lockheed in the mid 1940s.
General characteristics
* Crew: Two
* Capacity: 14 passengers
* Length: 56 ft 6 in (15.69 m)
* Wingspan: 74 ft 0 in (22.56 m)
* Height: 19 ft 10 in (6.05 m)
* Wing area: 502 ft² (46.6 m²)
* Empty weight: 11,361 lb (5,153 kg)
* Loaded weight: 16,000 lb (7,257 kg)
* Powerplant: 2× Wright 744C-7BA-1 seven cylinder radial engine, 700 hp (522 kW) each
Performance
* Maximum speed: 198 kn (228 mph, 367 km/h) at sea level
* Cruise speed: 163 kn (187 mph, 301 km/h)
* Range: 522 nmi (600 mi, 965 km)
* Service ceiling: 26,500 ft (8,075 m)
* Rate of climb: 1,325 ft/min (6.7 m/s)
Thursday, December 30, 2010
Lockheed L-1649A Starliner
TheLockheed L-1649A Starliner was the last model of the Lockheed constellation line.
General characteristics
* Crew: 5 flight crew, varying cabin crew
* Capacity: typically 62-95 passengers (109 in high-density configuration)
* Length: 116 ft 2 in (35.42 m)
* Wingspan: 126 ft 2 in (38.47 m)
* Height: 24 ft 9 in (7.54 m)
* Wing area: 1,654 ft² (153.7 m²)
* Empty weight: 79,700 lb (36,150 kg)
* Useful load: 65,300 lb (29,620 kg)
* Max takeoff weight: 137,500 lb (62,370kg)
* Powerplant: 4× Wright R-3350-DA3 Turbo Compound 18-cylinder supercharged radial engines, 3,250 hp (2,424 kW) each
Performance
* Maximum speed: 377 mph (327 kn, 607 km/h)
* Cruise speed: 340 mph (295 kn, 547 km/h) at 22,600 ft (6,890 m)
* Stall speed: 100 mph (87 kn, 160 km/h)
* Range: 5,400 mi (4,700 nmi, 8,700 km)
* Service ceiling: 24,000 ft (7,620 m)
* Rate of climb: 1,620 ft/min (8.23 m/s)
* Wing loading: 87.7 lb/ft² (428 kg/m²)
* Power/mass: 0.094 hp/lb (155 W/kg)
General characteristics
* Crew: 5 flight crew, varying cabin crew
* Capacity: typically 62-95 passengers (109 in high-density configuration)
* Length: 116 ft 2 in (35.42 m)
* Wingspan: 126 ft 2 in (38.47 m)
* Height: 24 ft 9 in (7.54 m)
* Wing area: 1,654 ft² (153.7 m²)
* Empty weight: 79,700 lb (36,150 kg)
* Useful load: 65,300 lb (29,620 kg)
* Max takeoff weight: 137,500 lb (62,370kg)
* Powerplant: 4× Wright R-3350-DA3 Turbo Compound 18-cylinder supercharged radial engines, 3,250 hp (2,424 kW) each
Performance
* Maximum speed: 377 mph (327 kn, 607 km/h)
* Cruise speed: 340 mph (295 kn, 547 km/h) at 22,600 ft (6,890 m)
* Stall speed: 100 mph (87 kn, 160 km/h)
* Range: 5,400 mi (4,700 nmi, 8,700 km)
* Service ceiling: 24,000 ft (7,620 m)
* Rate of climb: 1,620 ft/min (8.23 m/s)
* Wing loading: 87.7 lb/ft² (428 kg/m²)
* Power/mass: 0.094 hp/lb (155 W/kg)
Lockheed Constellation
The Lockheed Constellation ("Connie") is a propeller driven aircraft.
General characteristics
* Crew: 5 flight crew, varying cabin crew
* Capacity: typically 62-95 passengers (109 in high-density configuration)
* Length: 116 ft 2 in (35.42 m)
* Wingspan: 126 ft 2 in (38.47 m)
* Height: 24 ft 9 in (7.54 m)
* Wing area: 1,654 ft² (153.7 m²)
* Empty weight: 79,700 lb (36,150 kg)
* Useful load: 65,300 lb (29,620 kg)
* Max takeoff weight: 137,500 lb (62,370kg)
* Powerplant: 4× Wright R-3350-DA3 Turbo Compound 18-cylinder supercharged radial engines, 3,250 hp (2,424 kW) each
Performance
* Maximum speed: 377 mph (327 kn, 607 km/h)
* Cruise speed: 340 mph (295 kn, 547 km/h) at 22,600 ft (6,890 m)
* Stall speed: 100 mph (87 kn, 160 km/h)
* Range: 5,400 mi (4,700 nmi, 8,700 km)
* Service ceiling: 24,000 ft (7,620 m)
* Rate of climb: 1,620 ft/min (8.23 m/s)
* Wing loading: 87.7 lb/ft² (428 kg/m²)
* Power/mass: 0.094 hp/lb (155 W/kg)
General characteristics
* Crew: 5 flight crew, varying cabin crew
* Capacity: typically 62-95 passengers (109 in high-density configuration)
* Length: 116 ft 2 in (35.42 m)
* Wingspan: 126 ft 2 in (38.47 m)
* Height: 24 ft 9 in (7.54 m)
* Wing area: 1,654 ft² (153.7 m²)
* Empty weight: 79,700 lb (36,150 kg)
* Useful load: 65,300 lb (29,620 kg)
* Max takeoff weight: 137,500 lb (62,370kg)
* Powerplant: 4× Wright R-3350-DA3 Turbo Compound 18-cylinder supercharged radial engines, 3,250 hp (2,424 kW) each
Performance
* Maximum speed: 377 mph (327 kn, 607 km/h)
* Cruise speed: 340 mph (295 kn, 547 km/h) at 22,600 ft (6,890 m)
* Stall speed: 100 mph (87 kn, 160 km/h)
* Range: 5,400 mi (4,700 nmi, 8,700 km)
* Service ceiling: 24,000 ft (7,620 m)
* Rate of climb: 1,620 ft/min (8.23 m/s)
* Wing loading: 87.7 lb/ft² (428 kg/m²)
* Power/mass: 0.094 hp/lb (155 W/kg)
Lockheed Model 18 Lodestar
It is a passenger aircraft of World war 11 era.
General characteristics
* Crew: 3
* Capacity: 18 passengers
* Length: 49 ft 10 in (15.19 m)
* Wingspan: 65 ft 6 in (19.96 m)
* Height: 11 ft 10 in (3.6 m)
* Wing area: 551 ft² (51.2 m²)
* Empty weight: 12,500 lb (5,670 kg)
* Loaded weight: 17,500 lb (7,938 kg)
* Max takeoff weight: 21,000 lb (9,825 kg)
* Powerplant: 2× Wright R-1820-87 nine-cylinder air-cooled radial engines, 1,200 hp (895 kW) each
Performance
* Maximum speed: 266 mph (231 knots, 428 km/h) at 17,150 ft (5,230 m)
* Cruise speed: 200 mph (174 knots, 322 km/h)
* Range: 2,500 mi (2,174 nmi, 4,025 km)
* Service ceiling: 25,400 ft (7,740 m)
* Climb to 10,000 ft (3,050 m): 6.6 minutes
Armament
none
General characteristics
* Crew: 3
* Capacity: 18 passengers
* Length: 49 ft 10 in (15.19 m)
* Wingspan: 65 ft 6 in (19.96 m)
* Height: 11 ft 10 in (3.6 m)
* Wing area: 551 ft² (51.2 m²)
* Empty weight: 12,500 lb (5,670 kg)
* Loaded weight: 17,500 lb (7,938 kg)
* Max takeoff weight: 21,000 lb (9,825 kg)
* Powerplant: 2× Wright R-1820-87 nine-cylinder air-cooled radial engines, 1,200 hp (895 kW) each
Performance
* Maximum speed: 266 mph (231 knots, 428 km/h) at 17,150 ft (5,230 m)
* Cruise speed: 200 mph (174 knots, 322 km/h)
* Range: 2,500 mi (2,174 nmi, 4,025 km)
* Service ceiling: 25,400 ft (7,740 m)
* Climb to 10,000 ft (3,050 m): 6.6 minutes
Armament
none
Lockheed Model 14 Super Electra
The Lockheed Model 14 Super Electra or Lockheed 14, is a civil cargo and passenger aircraft built by the Lockheed Aircraft Corporation .
General characteristics
* Crew: two, pilot and co-pilot
* Capacity: 12 passengers
* Length: 44 ft 4 in (13.52 m)
* Wingspan: 65 ft 6 in (19.97 m)
* Height: 11 ft 5 in (3.48 m)
* Wing area: 551 ft² (51.2 m²)
* Empty weight: 10,750 lb (4,886 kg)
* Loaded weight: 15,650 lb (7,114 kg)
* Max takeoff weight: 17,500 lb (7,955 kg)
* Powerplant: 2× Wright SGR-1820-F62 radial engines, 760 hp (567 kW) each
Performance
* Maximum speed: 250 mph (402 km/h)
* Range: 2,125 mi (3,420 km)
* Service ceiling: 24,500 ft (7,649 m)
* Wing loading: 28 lb/ft² (139 kg/m²)
* Power/mass: 0.10 hp/lb (0.16 kW/kg)
General characteristics
* Crew: two, pilot and co-pilot
* Capacity: 12 passengers
* Length: 44 ft 4 in (13.52 m)
* Wingspan: 65 ft 6 in (19.97 m)
* Height: 11 ft 5 in (3.48 m)
* Wing area: 551 ft² (51.2 m²)
* Empty weight: 10,750 lb (4,886 kg)
* Loaded weight: 15,650 lb (7,114 kg)
* Max takeoff weight: 17,500 lb (7,955 kg)
* Powerplant: 2× Wright SGR-1820-F62 radial engines, 760 hp (567 kW) each
Performance
* Maximum speed: 250 mph (402 km/h)
* Range: 2,125 mi (3,420 km)
* Service ceiling: 24,500 ft (7,649 m)
* Wing loading: 28 lb/ft² (139 kg/m²)
* Power/mass: 0.10 hp/lb (0.16 kW/kg)
Lockheed Model 12 Electra Junior
It is also known as Lockheed 12 or L-12. It is an eight-seat, six-passenger all-metal twin-engine transport aircraft .
General characteristics
* Crew: two, pilot and co-pilot
* Capacity: six passengers
* Length: 36 ft 4 in (11.07 m)
* Wingspan: 49 ft 6 in (15.09 m)
* Height: 9 ft 9 in (2.97 m)
* Wing area: 352 ft² (32.7 m²)
* Empty weight: 5,765 lb (2,615 kg)
* Loaded weight: 8,650 lb (3,924 kg)
* Max takeoff weight: 9,200 lb (4,173 kg)
* Powerplant: 2× Pratt & Whitney R-985 Wasp Junior SB radial engines, 450 hp (336 kW) each
* Propellers: Two-bladed Hamilton Standard controllable-pitch or constant-speed propeller, 1 per engine
o Propeller diameter: 8.5 to 9 ft (2.6 to 2.75 m)
Performance
* Maximum speed: 225 mph (362 km/h, 196 kn) at 5,000 feet (1,500 m)
* Range: 800 mi (1,300 km, 700 nmi)
* Service ceiling: 22,900 ft (6,980 m)
* Rate of climb: 1,140 ft/min (427 m/min)
* Wing loading: 25 lb/ft² (120 kg/m²)
* Power/mass: 0.10 hp/lb (0.17 kW/kg)
General characteristics
* Crew: two, pilot and co-pilot
* Capacity: six passengers
* Length: 36 ft 4 in (11.07 m)
* Wingspan: 49 ft 6 in (15.09 m)
* Height: 9 ft 9 in (2.97 m)
* Wing area: 352 ft² (32.7 m²)
* Empty weight: 5,765 lb (2,615 kg)
* Loaded weight: 8,650 lb (3,924 kg)
* Max takeoff weight: 9,200 lb (4,173 kg)
* Powerplant: 2× Pratt & Whitney R-985 Wasp Junior SB radial engines, 450 hp (336 kW) each
* Propellers: Two-bladed Hamilton Standard controllable-pitch or constant-speed propeller, 1 per engine
o Propeller diameter: 8.5 to 9 ft (2.6 to 2.75 m)
Performance
* Maximum speed: 225 mph (362 km/h, 196 kn) at 5,000 feet (1,500 m)
* Range: 800 mi (1,300 km, 700 nmi)
* Service ceiling: 22,900 ft (6,980 m)
* Rate of climb: 1,140 ft/min (427 m/min)
* Wing loading: 25 lb/ft² (120 kg/m²)
* Power/mass: 0.10 hp/lb (0.17 kW/kg)
Lockheed Model 10 Electra
It is a monoplane with twin engine.
General characteristics
* Crew: 2
* Capacity: 10 passengers
* Length: 38 ft 7 in (11.8 m)
* Wingspan: 55 ft 0 in (16.8 m)
* Height: 10 ft 1 in (3.1 m)
* Wing area: 458 ft² (42.6 m²)
* Empty weight: 6,454 lb (2,930 kg)
* Loaded weight: 10,500 lb (4,760 kg)
* Powerplant: 2× Pratt & Whitney R-985 Wasp Junior SB, 450 hp (340 kW) each
Performance
* Maximum speed: 202 mph (325 km/h)
* Range: 713 mi (1,150 km)
* Service ceiling: 19,400 ft (5,910 m)
* Rate of climb: 1,000 ft/min (300 m/min)
* Wing loading: 22.9 lb/ft² (111.7 kg/m²)
* Power/mass: 11.7 lb/hp (142 W/kg)
General characteristics
* Crew: 2
* Capacity: 10 passengers
* Length: 38 ft 7 in (11.8 m)
* Wingspan: 55 ft 0 in (16.8 m)
* Height: 10 ft 1 in (3.1 m)
* Wing area: 458 ft² (42.6 m²)
* Empty weight: 6,454 lb (2,930 kg)
* Loaded weight: 10,500 lb (4,760 kg)
* Powerplant: 2× Pratt & Whitney R-985 Wasp Junior SB, 450 hp (340 kW) each
Performance
* Maximum speed: 202 mph (325 km/h)
* Range: 713 mi (1,150 km)
* Service ceiling: 19,400 ft (5,910 m)
* Rate of climb: 1,000 ft/min (300 m/min)
* Wing loading: 22.9 lb/ft² (111.7 kg/m²)
* Power/mass: 11.7 lb/hp (142 W/kg)
Lockheed Vega
It is a monoplane with monocoque fuselage built by lockheed.
General characteristics
* Crew: 1
* Length: 27 ft 6 in (8.38 m)
* Wingspan: 41 ft in (12.49 m)
* Height: 8 ft 6 in (2.59 m)
* Wing area: 259 sq ft (25.548 m2)
* Airfoil: Clark Y
* Empty weight: 2,565 lb (1,163 kg)
* Loaded weight: 4,500 lb (2,041 kg)
* Powerplant: 1× Pratt & Whitney Wasp R1340C, 500 hp (372.5 kW)
Performance
* Maximum speed: 185 mph (298 km/h)
* Cruise speed: 165 mph (265 km/h)
* Range: 725 mi (1,165 km)
* Service ceiling: 15,000 ft (4,570 m)
* Rate of climb: 1,300 ft/min (6.6 m/s)
Variants
Vega 1
Five-seat cabin monoplane, accommodation for one pilot and four passengers, powered by a 225-hp (168-kW) Wright J-5, J-5A, J-5AB or J-5C Whirlwind radial piston engine.
Vega 2
Five-seat cabin monoplane, powered by a 300-hp (224-kW) Wright J-6 Whirlwind radial piston engine.
Vega 2A
Redesignation of one Vega 2 aircraft, modified for higher gross weights operators.
Vega 2D
Redesignation of two Vega 1s and one Vega 2, each fitted with a 300-hp (224-kW) Pratt @ Whitney Wasp radial piston engine.
Vega 5
Improved version, powered by a 410-hp (306-kW) Wasp A, 450-hp (336-kW) Wasp B or 420-hp (313-kW) Wasp C1 radial piston engine.
Vega 5A Executive
Executive transport version, with a plush interior.
Vega 5B
Seven-seat passenger transport version, built for higher gross weight operations with commercial operators.
General characteristics
* Crew: 1
* Length: 27 ft 6 in (8.38 m)
* Wingspan: 41 ft in (12.49 m)
* Height: 8 ft 6 in (2.59 m)
* Wing area: 259 sq ft (25.548 m2)
* Airfoil: Clark Y
* Empty weight: 2,565 lb (1,163 kg)
* Loaded weight: 4,500 lb (2,041 kg)
* Powerplant: 1× Pratt & Whitney Wasp R1340C, 500 hp (372.5 kW)
Performance
* Maximum speed: 185 mph (298 km/h)
* Cruise speed: 165 mph (265 km/h)
* Range: 725 mi (1,165 km)
* Service ceiling: 15,000 ft (4,570 m)
* Rate of climb: 1,300 ft/min (6.6 m/s)
Variants
Vega 1
Five-seat cabin monoplane, accommodation for one pilot and four passengers, powered by a 225-hp (168-kW) Wright J-5, J-5A, J-5AB or J-5C Whirlwind radial piston engine.
Vega 2
Five-seat cabin monoplane, powered by a 300-hp (224-kW) Wright J-6 Whirlwind radial piston engine.
Vega 2A
Redesignation of one Vega 2 aircraft, modified for higher gross weights operators.
Vega 2D
Redesignation of two Vega 1s and one Vega 2, each fitted with a 300-hp (224-kW) Pratt @ Whitney Wasp radial piston engine.
Vega 5
Improved version, powered by a 410-hp (306-kW) Wasp A, 450-hp (336-kW) Wasp B or 420-hp (313-kW) Wasp C1 radial piston engine.
Vega 5A Executive
Executive transport version, with a plush interior.
Vega 5B
Seven-seat passenger transport version, built for higher gross weight operations with commercial operators.
Thursday, September 16, 2010
The Lockheed U-2
The Lockheed U-2, nicknamed "Dragon Lady", is a single-engine, very high-altitude reconnaissance aircraft operated by the United States Air Force and previously flown by the Central Intelligence Agency. It provides day and night, very high-altitude (70,000 feet / 21,000 meters), all-weather surveillance.The aircraft is also used for electronic sensor research and development, satellite calibration, and satellite data validation.
Role: High-altitude surveillance
Manufacturer: Lockheed Skunk Works
Designed by: Clarence "Kelly" Johnson
First flight: 1 August 1955
Introduction: 1957
Status: Active: 35
Reserve: 0
ANG: 0
Primary users: United States Air Force
Central Intelligence Agency
Republic of China Air Force
NASA
Number built: 86
General characteristics
* Crew: One
* Length: 63 ft (19.2 m)
* Wingspan: 103 ft (31.4 m)
* Height: 16 ft (4.88 m)
* Wing area: 1,000 ft² (92.9 m²)
* Aspect ratio: 14.3
* Empty weight: 14,300 lb (6,760 kg)
* Max takeoff weight: 40,000 lb (18,100 kg)
* Powerplant: 1× General Electric F118-101 turbofan, 19,000 lbf (84.5 kN)
Performance
* Maximum speed: 434 knots (500 mph, 805 km/h)
* Cruise speed: 373 knots (429 mph, 690 km/h)
* Range: 5,566 nmi (6,405 mi, 10,300 km)
* Service ceiling: 70,000+ ft (21,300+ m)
* Flight endurance: 12 hours
Role: High-altitude surveillance
Manufacturer: Lockheed Skunk Works
Designed by: Clarence "Kelly" Johnson
First flight: 1 August 1955
Introduction: 1957
Status: Active: 35
Reserve: 0
ANG: 0
Primary users: United States Air Force
Central Intelligence Agency
Republic of China Air Force
NASA
Number built: 86
General characteristics
* Crew: One
* Length: 63 ft (19.2 m)
* Wingspan: 103 ft (31.4 m)
* Height: 16 ft (4.88 m)
* Wing area: 1,000 ft² (92.9 m²)
* Aspect ratio: 14.3
* Empty weight: 14,300 lb (6,760 kg)
* Max takeoff weight: 40,000 lb (18,100 kg)
* Powerplant: 1× General Electric F118-101 turbofan, 19,000 lbf (84.5 kN)
Performance
* Maximum speed: 434 knots (500 mph, 805 km/h)
* Cruise speed: 373 knots (429 mph, 690 km/h)
* Range: 5,566 nmi (6,405 mi, 10,300 km)
* Service ceiling: 70,000+ ft (21,300+ m)
* Flight endurance: 12 hours
Lockheed Martin F-22 Raptor
The Lockheed Martin/Boeing F-22 Raptor is a single-seat, twin-engine fifth-generation fighter aircraft that uses stealth technology. It was designed primarily as an air superiority fighter, but has additional capabilities that include ground attack, electronic warfare, and signals intelligence roles. The high cost of the aircraft, a lack of clear air-to-air combat missions because of the lengthy delays in the Russian and Chinese fifth generation fighter programs, a US ban on Raptor exports, and the development of the cheaper and more versatile F-35 resulted in calls to end F-22 production
Role: Stealth air superiority fighter, multirole fighter
National origin: United States
Manufacturer: Lockheed Martin Aeronautics, Boeing Integrated Defense Systems
First flight: YF-22: 29 September 1990; F-22: 7 September 1997
Introduced: 15 December 2005
Status: In service
Primary user: United States Air Force
Number built: 166 as of September 2010 (187 planned)
Program cost: US$65 billion
Unit cost: US$150 million (flyaway cost for FY2009)
Developed from: Lockheed YF-22
Developed into: X-44 MANTA, FB-22
General characteristics
* Crew: 1
* Length: 62 ft 1 in (18.90 m)
* Wingspan: 44 ft 6 in (13.56 m)
* Height: 16 ft 8 in (5.08 m)
* Wing area: 840 ft² (78.04 m²)
* Airfoil: NACA 64A?05.92 root, NACA 64A?04.29 tip
* Empty weight: 43,430 lb (19,700 kg)
* Loaded weight: 64,460 lb (29,300 kg)
* Max takeoff weight: 83,500 lb (38,000 kg)
* Powerplant: 2× Pratt & Whitney F119-PW-100 Pitch Thrust vectoring turbofans
o Dry thrust: 23,500 lb (104 kN) each
o Thrust with afterburner: 35,000+ lb (156+ kN) each
* Fuel capacity: 18,000 lb (8,200 kg) internally,or 26,000 lb (11,900 kg) with two external fuel tanks
Performance
* Maximum speed:
o At altitude: Mach 2.25 (1,500 mph, 2,410 km/h)
o Supercruise: Mach 1.82 (1,220 mph, 1,963 km/h)
* Range: 1,600 nmi (1,840 mi, 2,960 km) with 2 external fuel tanks
* Combat radius: 410 nmi[188] (471 mi, 759 km)
* Ferry range: 2,000 mi (1,738 nmi, 3,219 km)
* Service ceiling: 65,000 ft (19,812 m)
* Wing loading: 77 lb/ft² (375 kg/m²)
* Thrust/weight: 1.08 (1.26 with loaded weight & 50% fuel)
* Maximum design g-load: -3.0/+9.0 g
Armament
* Guns: 1× 20 mm (0.787 in) M61A2 Vulcan 6-barreled Gatling cannon in starboard wing root, 480 rounds
* Air to air loadout:
o 6× AIM-120 AMRAAM
o 2× AIM-9 Sidewinder
* Air to ground loadout:
o 2× AIM-120 AMRAAM and
o 2× AIM-9 Sidewinder for self-protection, and one of the following:
+ 2× 1,000 lb (450 kg) JDAM or
+ 8× 250 lb (110 kg) GBU-39 Small Diameter Bombs
* Hard points: 4× under-wing pylon stations can be fitted to carry 600 US gallon drop tanks or weapons, each with a capacity of 5,000 lb (2,268 kg).
Avionics
* RWR (Radar warning receiver): 250 nmi (463 km) or more
* Radar: 125-150 miles (200-240 km) against 1 m2 (11 sq ft) targets (estimated range)
* Chemring MJU-39/40 flares for protection against IR missiles.
Role: Stealth air superiority fighter, multirole fighter
National origin: United States
Manufacturer: Lockheed Martin Aeronautics, Boeing Integrated Defense Systems
First flight: YF-22: 29 September 1990; F-22: 7 September 1997
Introduced: 15 December 2005
Status: In service
Primary user: United States Air Force
Number built: 166 as of September 2010 (187 planned)
Program cost: US$65 billion
Unit cost: US$150 million (flyaway cost for FY2009)
Developed from: Lockheed YF-22
Developed into: X-44 MANTA, FB-22
General characteristics
* Crew: 1
* Length: 62 ft 1 in (18.90 m)
* Wingspan: 44 ft 6 in (13.56 m)
* Height: 16 ft 8 in (5.08 m)
* Wing area: 840 ft² (78.04 m²)
* Airfoil: NACA 64A?05.92 root, NACA 64A?04.29 tip
* Empty weight: 43,430 lb (19,700 kg)
* Loaded weight: 64,460 lb (29,300 kg)
* Max takeoff weight: 83,500 lb (38,000 kg)
* Powerplant: 2× Pratt & Whitney F119-PW-100 Pitch Thrust vectoring turbofans
o Dry thrust: 23,500 lb (104 kN) each
o Thrust with afterburner: 35,000+ lb (156+ kN) each
* Fuel capacity: 18,000 lb (8,200 kg) internally,or 26,000 lb (11,900 kg) with two external fuel tanks
Performance
* Maximum speed:
o At altitude: Mach 2.25 (1,500 mph, 2,410 km/h)
o Supercruise: Mach 1.82 (1,220 mph, 1,963 km/h)
* Range: 1,600 nmi (1,840 mi, 2,960 km) with 2 external fuel tanks
* Combat radius: 410 nmi[188] (471 mi, 759 km)
* Ferry range: 2,000 mi (1,738 nmi, 3,219 km)
* Service ceiling: 65,000 ft (19,812 m)
* Wing loading: 77 lb/ft² (375 kg/m²)
* Thrust/weight: 1.08 (1.26 with loaded weight & 50% fuel)
* Maximum design g-load: -3.0/+9.0 g
Armament
* Guns: 1× 20 mm (0.787 in) M61A2 Vulcan 6-barreled Gatling cannon in starboard wing root, 480 rounds
* Air to air loadout:
o 6× AIM-120 AMRAAM
o 2× AIM-9 Sidewinder
* Air to ground loadout:
o 2× AIM-120 AMRAAM and
o 2× AIM-9 Sidewinder for self-protection, and one of the following:
+ 2× 1,000 lb (450 kg) JDAM or
+ 8× 250 lb (110 kg) GBU-39 Small Diameter Bombs
* Hard points: 4× under-wing pylon stations can be fitted to carry 600 US gallon drop tanks or weapons, each with a capacity of 5,000 lb (2,268 kg).
Avionics
* RWR (Radar warning receiver): 250 nmi (463 km) or more
* Radar: 125-150 miles (200-240 km) against 1 m2 (11 sq ft) targets (estimated range)
* Chemring MJU-39/40 flares for protection against IR missiles.
Friday, September 3, 2010
Lockheed Martin F-35 Lightning II
The Lockheed Martin F-35 Lightning II is a fifth-generation, single-seat, single-engine stealth multirole fighter that can perform close air support, tactical bombing, and air defense missions.
Role: Stealth multirole fighter
First flight: 15 December 2006
Introduction: 2014 (USMC), 2014 (USAF), 2016 (USN)
Status: Under development, in flight testing
Produced: 2003–present
Number built: 13 flight-test aircraft, 15 LRIP aircraft on order.
Unit cost: US$191.9 million (flyaway cost for FY 2010)
Developed from: Lockheed Martin X-35
Maximum speed: Mach 1.67 (1,283 mph, 2,065 km/h)
Range: 1,200 nmi (2,220 km) on internal fuel
Combat radius: 590 nmi (1,090 km) on internal fuel
Service ceiling: 60,000 ft(18,288 m)
Rate of climb: classified (not publicly available)
Wing loading: 91.4 lb/ft² (446 kg/m²)
Thrust/weight:
With full fuel: 0.87
With 50% fuel: 1.07
g-Limits: 9 g
Armament:
Guns: 1 × 25 mm (0.984 in) GAU-22/A cannon, internally mounted with 180 rounds
Hardpoints: 6× external pylons on wings with a capacity of 15,000 lb (6,800 kg) and 2 × internal bays with 2 pylons each for a total weapons payload of 18,000 lb (8,100 kg) and provisions to carry combinations of:
Missiles:
Air-to-air: AIM-9X Sidewinder, IRIS-T, Joint Dual Role Air Dominance Missile (JDRADM) (after 2020)
Air-to-ground: AGM-154 JSOW, AGM-158 JASSM
Bombs:
Mark 84, Mark 83 and Mark 82 GP bombs
Mk.20 Rockeye II cluster bomb
Wind Corrected Munitions Dispenser capable
Paveway-series laser-guided bombs
Small Diameter Bomb (SDB)
JDAM-series
B61 nuclear bomb (for F-35A in 2017)
Avionics:Northrop Grumman Electronic Systems AN/APG-81 AESA radar
Role: Stealth multirole fighter
First flight: 15 December 2006
Introduction: 2014 (USMC), 2014 (USAF), 2016 (USN)
Status: Under development, in flight testing
Produced: 2003–present
Number built: 13 flight-test aircraft, 15 LRIP aircraft on order.
Unit cost: US$191.9 million (flyaway cost for FY 2010)
Developed from: Lockheed Martin X-35
Maximum speed: Mach 1.67 (1,283 mph, 2,065 km/h)
Range: 1,200 nmi (2,220 km) on internal fuel
Combat radius: 590 nmi (1,090 km) on internal fuel
Service ceiling: 60,000 ft(18,288 m)
Rate of climb: classified (not publicly available)
Wing loading: 91.4 lb/ft² (446 kg/m²)
Thrust/weight:
With full fuel: 0.87
With 50% fuel: 1.07
g-Limits: 9 g
Armament:
Guns: 1 × 25 mm (0.984 in) GAU-22/A cannon, internally mounted with 180 rounds
Hardpoints: 6× external pylons on wings with a capacity of 15,000 lb (6,800 kg) and 2 × internal bays with 2 pylons each for a total weapons payload of 18,000 lb (8,100 kg) and provisions to carry combinations of:
Missiles:
Air-to-air: AIM-9X Sidewinder, IRIS-T, Joint Dual Role Air Dominance Missile (JDRADM) (after 2020)
Air-to-ground: AGM-154 JSOW, AGM-158 JASSM
Bombs:
Mark 84, Mark 83 and Mark 82 GP bombs
Mk.20 Rockeye II cluster bomb
Wind Corrected Munitions Dispenser capable
Paveway-series laser-guided bombs
Small Diameter Bomb (SDB)
JDAM-series
B61 nuclear bomb (for F-35A in 2017)
Avionics:Northrop Grumman Electronic Systems AN/APG-81 AESA radar
Lockheed P-80 Shooting Star
The Lockheed P-80 Shooting Star was the first jet fighter used operationally by the United States Army Air Forces
Role: Jet Fighter
National origin: United States
Manufacturer: Lockheed
Designed by: Clarence "Kelly" Johnson
First flight: 8 January 1944
Introduction: 1945
Status: Retired
Primary users: United States Air Force, United States Navy
Number built: 1,715
Unit cost: US$110,000 in 1945
Variants: T-33 Shooting Star, F-94 Starfire
General characteristics
Crew: One
Length: 34 ft 5 in (10.49 m)
Wingspan: 38 ft 9 in (11.81 m)
Height: 11 ft 3 in (3.43 m)
Wing area: 237.6 ft² (22.07 m²)
Aspect ratio: 6.37
Empty weight: 8,420 lb (3,819 kg)
Loaded weight: 12,650 lb (5,738 kg)
Max takeoff weight: 16,856 lb (7,646 kg)
Powerplant: 1× Allison J33-A-35 centrifugal compressor turbojet, 5,400 lbf (24.0 kN)
Zero-lift drag coefficient: 0.0134
Drag area: 3.2 ft² (0.30 m²)
Performance
Maximum speed: 600 mph (965 km/h)
Cruise speed: 410 mph (660 km/h)
Range: 1,200 mi (1,930 km)
Service ceiling: 46,000 ft (14,000 m)
Rate of climb: 4,580 ft/min (23.3 m/s) 5.5 min to 20,000 ft (6,100 m)
Wing loading: 53 lb/ft² (260 kg/m²)
Thrust/weight: 0.43 Lift-to-drag ratio: 17.7
Armament
Guns: 6 × 0.50 in (12.7 mm) M2 Browning machine guns (300 rpg)
Rockets: 8 × unguided rockets
Bombs: 2 × 1,000 lb (454 kg) bombs
Wednesday, September 1, 2010
Lockheed P-38 Lightning
Specifications (P-38L)
General characteristics
Crew: One
Length: 37 ft 10 in (11.53 m)
Wingspan: 52 ft 0 in (15.85 m)
Height: 12 ft 10 in (3.91 m)
Wing area: 327.5 ft² (30.43 m²)
Airfoil: NACA 23016 / NACA 4412
Empty weight: 12,800 lb (5,800 kg)
Loaded weight: 17,500 lb (7,940 kg)
Max takeoff weight: 21,600 lb (9,798 kg)
Powerplant: 2× Allison V-1710-111/113 V-12 piston engine, 1,725 hp (1,194 kW) each Zero-lift drag coefficient: 0.0268
Drag area: 8.78 ft² (0.82 m²)
Aspect ratio: 8.26
Performance
Maximum speed: 443 mph (712 km/h) on War Emergency
Power: 1,725 hp at 64 inHG and 28,000 ft (8530 m)
Stall speed: 105 mph (170 km/h) Range: 1,300 mi combat (1,770 km / 3,640 km)
Service ceiling: 44,000 ft (13,400 m)
Rate of climb: 4,750 ft/min (1,448 m/min)
maximum Wing loading: 53.4 lb/ft² (260.9 kg/m²)
Power/mass: 0.16 hp/lb (0.27 kW/kg) Lift-to-drag ratio: 13.5
General characteristics
Crew: One
Length: 37 ft 10 in (11.53 m)
Wingspan: 52 ft 0 in (15.85 m)
Height: 12 ft 10 in (3.91 m)
Wing area: 327.5 ft² (30.43 m²)
Airfoil: NACA 23016 / NACA 4412
Empty weight: 12,800 lb (5,800 kg)
Loaded weight: 17,500 lb (7,940 kg)
Max takeoff weight: 21,600 lb (9,798 kg)
Powerplant: 2× Allison V-1710-111/113 V-12 piston engine, 1,725 hp (1,194 kW) each Zero-lift drag coefficient: 0.0268
Drag area: 8.78 ft² (0.82 m²)
Aspect ratio: 8.26
Performance
Maximum speed: 443 mph (712 km/h) on War Emergency
Power: 1,725 hp at 64 inHG and 28,000 ft (8530 m)
Stall speed: 105 mph (170 km/h) Range: 1,300 mi combat (1,770 km / 3,640 km)
Service ceiling: 44,000 ft (13,400 m)
Rate of climb: 4,750 ft/min (1,448 m/min)
maximum Wing loading: 53.4 lb/ft² (260.9 kg/m²)
Power/mass: 0.16 hp/lb (0.27 kW/kg) Lift-to-drag ratio: 13.5
Lockheed C-130 Hercules
Specifications (C-130H)
General characteristics
Crew: 5 (two pilots, navigator, flight engineer and loadmaster)
Capacity:92 passengers or 64 airborne troops or 74 litter patients with 2 medical personnel or 6 pallets or 2–3 HMMWVs or 2 M113 armored personnel carrier
Payload: 45,000 lb (20,000 kg)
Length: 97 ft 9 in (29.8 m)
Wingspan: 132 ft 7 in (40.4 m)
Height: 38 ft 3 in (11.6 m)
Wing area: 1,745 ft² (162.1 m²)
Empty weight: 75,800 lb (34,400 kg)
Useful load: 72,000 lb (33,000 kg)
Max takeoff weight: 155,000 lb (70,300 kg)
Powerplant: 4× Allison T56-A-15 turboprops, 4,590 shp (3,430 kW) each Performance
Maximum speed: 320 knots (366 mph, 592 km/h) at 20,000 ft (6,060 m)
Cruise speed: 292 kn (336 mph, 540 km/h) Range: 2,050 nmi (2,360 mi, 3,800 km)
Service ceiling: 23,000 ft (7,000 m)
Rate of climb: 1,830 ft/min (9.3 m/s)
Takeoff distance: 3,586 ft (1,093 m) at 155,000 lb (70,300 kg)
max gross weight; 1,400 ft (427 m) at 80,000 lb (36,300 kg)
General characteristics
Crew: 5 (two pilots, navigator, flight engineer and loadmaster)
Capacity:92 passengers or 64 airborne troops or 74 litter patients with 2 medical personnel or 6 pallets or 2–3 HMMWVs or 2 M113 armored personnel carrier
Payload: 45,000 lb (20,000 kg)
Length: 97 ft 9 in (29.8 m)
Wingspan: 132 ft 7 in (40.4 m)
Height: 38 ft 3 in (11.6 m)
Wing area: 1,745 ft² (162.1 m²)
Empty weight: 75,800 lb (34,400 kg)
Useful load: 72,000 lb (33,000 kg)
Max takeoff weight: 155,000 lb (70,300 kg)
Powerplant: 4× Allison T56-A-15 turboprops, 4,590 shp (3,430 kW) each Performance
Maximum speed: 320 knots (366 mph, 592 km/h) at 20,000 ft (6,060 m)
Cruise speed: 292 kn (336 mph, 540 km/h) Range: 2,050 nmi (2,360 mi, 3,800 km)
Service ceiling: 23,000 ft (7,000 m)
Rate of climb: 1,830 ft/min (9.3 m/s)
Takeoff distance: 3,586 ft (1,093 m) at 155,000 lb (70,300 kg)
max gross weight; 1,400 ft (427 m) at 80,000 lb (36,300 kg)
Tuesday, August 31, 2010
Blackburn Botha
| First flight | 28 December 1938 | |
|---|---|---|
| Introduced | 12 December 1939 | |
| Retired | September 1944 | |
| Number built | 580 | |
The Blackburn B.26 Botha was a competitor to the Bristol, and entered service with the RAF in 1939. It was underpowered and was quickly withdrawn from operations.
In service, the Botha proved to be severely underpowered and unstable and there were a number of fatal crashes in 1940. Both airframe and engine were subject to further development work, but it was decided to withdraw the type from front-line service. At this point, the Air Staff made the ill-advised decision to transfer the surviving aircraft to training units, which inevitably resulted in further casualties.
The type was finally retired in September 1944. In total, 580 aircraft were built.
Variants
- Botha Mk I : Four-seat reconnaissance, torpedo bomber aircraft.
- Botha TT Mk I : Target tug aircraft.
General characteristics
- Crew: 4
- Length: 51 ft 1.5 in (15.58 m)
- wingspan: 59 ft (17.98 m)
- Height: 14 ft 7.5 in (4.46 m)
- Wing area: 518 ft² (48.12 m²)
- Max take off weight: 18,450 lb (8,369 kg)
- Powerplant: 2× Bristol Perseus radial engine, 930 hp (694 kW) each
- 3 × 0.303 in (7.7 mm) machine guns (one fixed forward-firing, two in dorsal turret)
- internal torpedo, depth charges or bombs up to 2,000 lb (907 kg)
Mil Mi-46
- The Mil Mi-46 is a projected passenger/cargo/flying crane aircraft
- Announced first in 1992
- . The aircraft was split into two versions: Mi-46T and Mi-46K.
- The Mi-46T was the passenger/cargo transport version.
- The Mi-46T just half the weight of the Mi-26,
- The Mi-46T fit to replace the aging Mi-26.
- The Mi-46K was the flying crane version fit to replace the Mi-10K.
Boeing Bird of Prey
las / Boeing
| Role | Stealth testbed |
|---|---|
| Manufacturer | Mc Dnnnell Douglas / Boeing |
| First flight | 1996 |
| Retired | 1999 |
| Status | Experimental |
| Number built | 1 |
- Crew: 1
- Length: approximately 47 ft (14.30 m)
- wingspan: approximately 23 ft (7.00 m)
- Height: 6 ft (1.83 m)
- max take off weight: 7,380 lb (3,350 kg)
- Powerplant: 1× Pratt & Whitney Canada JT 15D - 5C , 2,900 lbf (12.9 kN)
Performance
- max speed: 260 knots (482 km/h)
- service ceiling: 20,000 ft (6,100 m)
The Bird of Prey aircraft was developed intending to demonstrate stealth technology . it was a low cost program ( a price of $67 million) compared to many other programs . It developed technology and materials which would later be used on Boeing's X-45 unmanned combat air vehicle. It is characterized as a technology demonstrator.Development of the Bird of Prey began in 1992 by McDonnell Douglas's Phantom Works division for special projects. The first flight was in 1996, and 39 more were performed through the program's conclusion in 1999.The Bird of Prey is designed to prevent shadows and is believed to have been used to test active camouflage , which would involve its surfaces changing color or luminosity to match the surroundings.
Tuesday, July 13, 2010
The AASI Jetcruzer
The AASI Jetcruzer
Country of origin :United States of America
Powerplants :
One rear mounted 1172kW (1572shp) Pratt & Whitney Canada PT6A-66A turboprop driving a five blade constant speed Hartzell propeller.
Performance :
Max cruising speed 576km/h (318kt). Service ceiling 30,000ft. Max range at economical cruising speed with reserves 2574km (1391nm).
Weights :Max takeoff 2495kg (5500lb).
Dimensions :Wing span 12.85m (42ft 2in), length approx 10.5m (34.4ft).
Capacity :
Typical accommodation for six including pilot. Can be configured for ambulance, cargo and other utility work. Optional aft lavatory.
Production :
450 - 3 were built. 500 - by November 2001, 2 had been converted from 450s, 1 new one was built, and 197 were on order. Basic unit price (2001) $US1.495.000.
Type :Business and utility transport
History :
The innovative Jetcruzer 500 is designed to be a high speed low cost single engine corporate turboprop and is the product of California based Advanced Aerodynamics and Structures Inc (AASI).
The Jetcruzer 500 is based on the smaller, unpressurised Jetcruzer 450. Early design work for what would become the Jetcruzer 450 began in 1983. Construction of an Allison 250-C20S powered prototype began in 1988. It flew for the first time on January 11 1989.
The preproduction prototype first flew April 1991, and the first production standard Jetcruzer 450 on September 13 1992. When FAA Part 23 certification was granted on June 14 1994 the Jetcruzer became the first aircraft in the world to be certificated as spin resistant.
AASI elected not to place the 450 into production and instead focused its efforts on the pressurised 500. Initial work was on the 500P, which featured a modest 25cm (10in) fuselage stretch, but AASI instead decided to enlarge the design further. The definitive Jetcruzer features a 1.83m (6ft) fuselage stretch over the 450 (increasing cabin length by 90cm (3ft), plus a significantly more powerful PT6A66 turboprop driving a five (rather than three) blade prop, pressurisation to 30,000ft, an airstair entry door on the right hand side and additional cabin windows.
First flight of the prototype 500 (the modified preproduction prototype 450) was in August 22 1997, followed by the second prototype (the modified production 450) on November 7 1997.
Other notable Jetcruzer 500 design features include its canard configuration (which allows the main wing to be positioned further aft than normal, so the wing spars do not intrude into the cabin), lack of flaps (reducing pilot work load and manufacturing costs and saving weight), and optional EFIS avionics. Like the 450 the 500 will be certificated as spin resistant. The fuselage is made from composites while the wing and canard are aluminium.
On February 8 2002, AASI announced that it was taking over the Mooney assets, and that the name Mooney would be used for the combined companies. Headquarters, development, and marketing would remain at AASI's facility at Long Beach in California, but production of the Jetcruzer would be at Mooney's Kerrville, Texas plant.
The company is also working on the Stratocruzer 1250, a 13 place twin WilliamsRolls FJ-44 powered light corporate jet development.
Country of origin :United States of America
Powerplants :
One rear mounted 1172kW (1572shp) Pratt & Whitney Canada PT6A-66A turboprop driving a five blade constant speed Hartzell propeller.
Performance :
Max cruising speed 576km/h (318kt). Service ceiling 30,000ft. Max range at economical cruising speed with reserves 2574km (1391nm).
Weights :Max takeoff 2495kg (5500lb).
Dimensions :Wing span 12.85m (42ft 2in), length approx 10.5m (34.4ft).
Capacity :
Typical accommodation for six including pilot. Can be configured for ambulance, cargo and other utility work. Optional aft lavatory.
Production :
450 - 3 were built. 500 - by November 2001, 2 had been converted from 450s, 1 new one was built, and 197 were on order. Basic unit price (2001) $US1.495.000.
Type :Business and utility transport
History :
The innovative Jetcruzer 500 is designed to be a high speed low cost single engine corporate turboprop and is the product of California based Advanced Aerodynamics and Structures Inc (AASI).
The Jetcruzer 500 is based on the smaller, unpressurised Jetcruzer 450. Early design work for what would become the Jetcruzer 450 began in 1983. Construction of an Allison 250-C20S powered prototype began in 1988. It flew for the first time on January 11 1989.
The preproduction prototype first flew April 1991, and the first production standard Jetcruzer 450 on September 13 1992. When FAA Part 23 certification was granted on June 14 1994 the Jetcruzer became the first aircraft in the world to be certificated as spin resistant.
AASI elected not to place the 450 into production and instead focused its efforts on the pressurised 500. Initial work was on the 500P, which featured a modest 25cm (10in) fuselage stretch, but AASI instead decided to enlarge the design further. The definitive Jetcruzer features a 1.83m (6ft) fuselage stretch over the 450 (increasing cabin length by 90cm (3ft), plus a significantly more powerful PT6A66 turboprop driving a five (rather than three) blade prop, pressurisation to 30,000ft, an airstair entry door on the right hand side and additional cabin windows.
First flight of the prototype 500 (the modified preproduction prototype 450) was in August 22 1997, followed by the second prototype (the modified production 450) on November 7 1997.
Other notable Jetcruzer 500 design features include its canard configuration (which allows the main wing to be positioned further aft than normal, so the wing spars do not intrude into the cabin), lack of flaps (reducing pilot work load and manufacturing costs and saving weight), and optional EFIS avionics. Like the 450 the 500 will be certificated as spin resistant. The fuselage is made from composites while the wing and canard are aluminium.
On February 8 2002, AASI announced that it was taking over the Mooney assets, and that the name Mooney would be used for the combined companies. Headquarters, development, and marketing would remain at AASI's facility at Long Beach in California, but production of the Jetcruzer would be at Mooney's Kerrville, Texas plant.
The company is also working on the Stratocruzer 1250, a 13 place twin WilliamsRolls FJ-44 powered light corporate jet development.
Wednesday, July 7, 2010
McDonnell Douglas F-15 Eagle
The McDonnell Douglas (now Boeing) F-15 Eagle is a twin-engine, all-weather tactical fighter designed to gain and maintain air superiority in aerial combat. It is considered among the most successful modern fighters with over 100 aerial combat victories with no losses in dogfights.
- Role:Air superiority fighter
Manufacturer:McDonnell Douglas, Boeing IDS
First flight:27 July 1972
Introduction:9 January 1976
Status:Active
Primary users:United States Air Force, Japan Air Self-Defense Force, Royal Saudi Air Force, Israeli Air Force
Number built:F-15A/B/C/D/J/DJ: 1,198
Unit cost:F-15A/B: US$27.9 million (1998),F-15C/D: US$29.9 million (1998)
Variants:F-15E Strike Eagle, F-15SE Silent Eagle, F-15 S/MTD - General characteristics
Crew: 1
Length: 63 ft 9 in (19.43 m)
Wingspan: 42 ft 10 in (13.05 m)
Height: 18 ft 6 in (5.63 m)
Wing area: 608 ft² (56.5 m²)
Airfoil: NACA 64A006.6 root, NACA 64A203 tip
Empty weight: 28,000 lb (12,700 kg)
Loaded weight: 44,500 lb (20,200 kg)
Max takeoff weight: 68,000 lb (30,845 kg)
Powerplant: 2× Pratt & Whitney F100-100, -220 or -229 afterburning turbofans
Dry thrust: 17,450 lbf (77.62 kN) each
Thrust with afterburner: 25,000 lbf for -220; 29,000 lbf for -229 (111.2 kN for -220; 129.0 kN for -229) each - Performance
Maximum speed:
High altitude: Mach 2.5+ (1,650+ mph, 2,660+ km/h)
Low altitude: Mach 1.2 (900 mph, 1,450 km/h)
Combat radius: 1,061 nmi (1,222 mi, 1,967 km) for interdiction mission
Ferry range: 3,450 mi (3,000 nmi, 5,550 km) with conformal fuel tanks and three external fuel tanks
Service ceiling: 65,000 ft (20,000 m)
Rate of climb: >50,000 ft/min (254 m/s)
Wing loading: 73.1 lb/ft² (358 kg/m²)
Thrust/weight: 1.12 (-220), 1.30 (-229) - Armament
Guns: 1× internally mounted 20 mm (0.787 in) M61A1 gatling gun, 940 rounds
Hardpoints: four wing, four fuselage, two wing stations, centerline station, optional fuselage pylons with a capacity of 16,000 lb (7,300 kg)
Missiles:
AIM-7 Sparrow
AIM-120 AMRAAM
AIM-9 Sidewinders - Avionics
Radar:
Raytheon AN/APG-63 or AN/APG-70 or
Although several F-15C aircraft were produced with APG-70 radar, all have been retrofitted to the AN/APG-63(V)1 configuration
Raytheon AN/APG-63(V)1 or
Raytheon AN/APG-63(V)2 Active Electronically Scanned Array (AESA) or
Raytheon AN/APG-63(V)3 Active Electronically Scanned Array (AESA)
Both active AF and ANG F-15Cs will receive another (up to) 48 V3 units between 2009-2015, over the existing 19 aircraft.
Countermeasures:
AN/APX-76 or AN/APX-119 Identify Friend/Foe (IFF) interrogator
Magnavox AN/ALQ-128 Electronic Warfare Warning Set (EWWS) -part of Tactical Electronic Warfare Systems (TEWS)
Loral AN/ALR-56 Radar Warning Receiver (RWR)-part of Tactical Electronic Warfare Systems (TEWS)
Northrop ALQ-135 Internal Countermeasures System (ICS) - part of Tactical Electronic Warfare Systems (TEWS)
AN/ALE-45 chaff/flare dispensers
Pratt & Whitney F100 turbofan engines of an F-15C Eagle
Others:
Joint Helmet Mounted Cueing System
MXU-648 Cargo/Travel Pod - to carry personal belongings, and small pieces of maintenance equipment.
Lockheed Martin F-22 Raptor
The Lockheed Martin/Boeing F-22 Raptor is a single-seat, twin-engine fifth-generation fighter aircraft that uses stealth technology. It was designed primarily as an air superiority fighter, but has additional capabilities that include ground attack, electronic warfare, and signals intelligence.
Role:Stealth Air superiority fighter, multirole fighter
National origin:United States
Manufacturer:
Lockheed Martin Aeronautics
Boeing Integrated Defense Systems
First flight:
YF-22: 29 September 1990
F-22: 7 September 1997
Introduced:15 December 2005
Status:In service
Primary user:United States Air Force
Number built:168 as of May 2010 (187 planned)
Program cost:US$65 billion
Unit cost:US$150 million(2009 flyaway cost)
Developed into:X-44 MANTA, FB-22
Role:Stealth Air superiority fighter, multirole fighter
National origin:United States
Manufacturer:
Lockheed Martin Aeronautics
Boeing Integrated Defense Systems
First flight:
YF-22: 29 September 1990
F-22: 7 September 1997
Introduced:15 December 2005
Status:In service
Primary user:United States Air Force
Number built:168 as of May 2010 (187 planned)
Program cost:US$65 billion
Unit cost:US$150 million(2009 flyaway cost)
Developed into:X-44 MANTA, FB-22
- General characteristics
Crew: 1
Length: 62 ft 1 in (18.90 m)
Wingspan: 44 ft 6 in (13.56 m)
Height: 16 ft 8 in (5.08 m)
Wing area: 840 ft² (78.04 m²)
Airfoil: NACA 64A?05.92 root, NACA 64A?04.29 tip
Empty weight: 43,430 lb (19,700 kg)
Loaded weight: 64,460 lb (29,300 kg)
Max takeoff weight: 83,500 lb (38,000 kg)
Powerplant: 2× Pratt & Whitney F119-PW-100 Pitch Thrust vectoring turbofans
Dry thrust: 23,500 lb (104 kN) each
Thrust with afterburner: 35,000+ lb (156+ kN) each
Fuel capacity: 18,000 lb (8,200 kg) internally, or 26,000 lb (11,900 kg) with two external fuel tanks - Performance
Maximum speed:
At altitude: Mach 2.25 (1,500 mph, 2,410 km/h)
Supercruise: Mach 1.82 (1,220 mph, 1,963 km/h)
Range: 1,600 nmi (1,840 mi, 2,960 km) with 2 external fuel tanks
Combat radius: 410 nmi (471 mi, 759 km)
Ferry range: 2,000 mi (1,738 nmi, 3,219 km)
Service ceiling: 65,000 ft (19,812 m)
Wing loading: 77 lb/ft² (375 kg/m²)
Thrust/weight: 1.08 (1.26 with loaded weight & 50% fuel)
Maximum design g-load: -3.0/+9.0 g - Armament
Guns: 1× 20 mm (0.787 in) M61A2 Vulcan gatling gun in starboard wing root, 480 rounds
Air to air loadout:
6× AIM-120 AMRAAM
2× AIM-9 Sidewinder
Air to ground loadout:
2× AIM-120 AMRAAM and
2× AIM-9 Sidewinder for self-protection, and one of the following:
2× 1,000 lb (450 kg) JDAM or
2× Wind Corrected Munitions Dispensers (WCMDs) or
8× 250 lb (110 kg) GBU-39 Small Diameter Bombs
Hardpoints: 4× under-wing pylon stations can be fitted to carry 600 US gallon drop tanks or weapons, each with a capacity of 5,000 lb (2,268 kg). - Avionics
RWR (Radar warning receiver): 250 nmi (463 km) or more
Radar: 125-150 miles (200-240 km) against 1 m2 (11 sq ft) targets (estimated range)
Chemring MJU-39/40 flares for protection against IR missiles.
Grumman F-14 Tomcat
The Grumman F-14 Tomcat is a supersonic, twin-engine, two-seat, variable-sweep wing fighter aircrat.
- Role:Interceptor, multirole fighter aircraft
Manufacturer:Grumman
First flight:21 December 1970
Introduction:September 1974
Retired:US Navy: 22 September 2006
Status:Active service with Iran
Primary users:United States Navy (former)Islamic Republic of Iran Air Force
Number built:712
Unit cost:US$38 million in 1998
General characteristics
Crew: 2 (Pilot and Radar Intercept Officer)
Length: 62 ft 9 in (19.1 m)
Wingspan:
Spread: 64 ft (19.55 m)
Swept: 38 ft (11.58 m)
Height: 16 ft (4.88 m)
Wing area: 565 ft² (54.5 m²)
Airfoil: NACA 64A209.65 mod root, 64A208.91 mod tip
Empty weight: 43,735 lb (19,838 kg)
Loaded weight: 61,000 lb (27,700 kg)
Max takeoff weight: 74,350 lb (33,720 kg)
Powerplant: 2× General Electric F110-GE-400 afterburning turbofans
Dry thrust: 13,810 lbf (61.4 kN) each
Thrust with afterburner: 27,800 lbf (124.7 kN) each
Maximum fuel capacity: 16,200 lb internal; 20,000 lb with 2x 267 gallon external tanks
Performance
Maximum speed: Mach 2.34 (1,544 mph, 2,485 km/h) at high altitude
Combat radius: 500 nmi (575 mi, 926 km)
Ferry range: 1,600 nmi (1,840 mi, 2,960 km)
Service ceiling: 50,000 ft (15,200 m)
Rate of climb: >45,000 ft/min (229 m/s)
Wing loading: 113.4 lb/ft² (553.9 kg/m²)
Thrust/weight: 0.91
Armament
Guns: 1× 20 mm (0.787 in) M61 Vulcan Gatling Gun, with 675 rounds
Hardpoints: 10 total: 6× under-fuselage, 2× under nacelles and 2× on wing gloves with a capacity of 14,500 lb (6,600 kg) of ordnance and fuel tanks
Missiles:
Air-to-air missiles: AIM-54 Phoenix, AIM-7 Sparrow, AIM-9 Sidewinder
Loading configurations:
2× AIM-9 + 6× AIM-54 (Rarely used due to weight stress on airframe)
2× AIM-9 + 2× AIM-54 + 3× AIM-7 (Most common load during Cold War era)
2× AIM-9 + 4× AIM-54 + 2× AIM-7
2× AIM-9 + 6× AIM-7
4× AIM-9 + 4× AIM-54
4× AIM-9 + 4× AIM-7
Bombs:
JDAM Precision-guided munition (PGMs)
Paveway series of Laser guided bombs
Mk 80 series of unguided iron bombs
Mk 20 Rockeye II
Others:
LANTIRN targeting pod
2× 267 US gallon drop tanks for extended range/loitering time
Avionics
Hughes AN/APG-71 radar
AN/ASN-130 INS, IRST, TCS
Remotely Operated Video Enhanced Receiver (ROVER) upgrade
Vickers F.B 5 "Gun Bus"
Role:Fighter
Manufacturer:Vickers Limited
First flight:17 July 1914
Introduced:5 February 1915
Retired:1916 (mainly coz of lack of speed)
Primary users:Royal Flying Corps Aéronautique Militaire
Number built:224
General characteristics
Crew: Two, pilot & observer/gunner
Length: 27 ft 2 in (8.28 m)
Wingspan: 36 ft 6 in (11.13 m)
Height: 11 ft 0 in (3.35 m)
Wing area: 382 ft² (35.5 m²)
Empty weight: 1,220 lb (555 kg)
Loaded weight: 2,050 lb (930 kg)
Powerplant: 1× Gnome Monosoupape 9-cylinder rotary engine, 100 hp (75 kW)
Performance
Maximum speed: 70 mph (61 knots, 113 km/h) at 5,000 ft (1,520 m)
Range: 250 mi (217 NM, 403 km)
Service ceiling: 9,000 ft (2,743 m)
Wing loading: 5.4 lb/ft² (26 kg/m²)
Power/mass: 0.05 hp/lb (0.08 kW/kg)
Endurance 4 hours 30 minutes [9]
Climb to 5,000 ft (1,520 m): 16 min
Armament
1 × 0.303 in (7.7 mm) drum-fed Lewis gun in observer's cockpit
Manufacturer:Vickers Limited
First flight:17 July 1914
Introduced:5 February 1915
Retired:1916 (mainly coz of lack of speed)
Primary users:Royal Flying Corps Aéronautique Militaire
Number built:224
General characteristics
Crew: Two, pilot & observer/gunner
Length: 27 ft 2 in (8.28 m)
Wingspan: 36 ft 6 in (11.13 m)
Height: 11 ft 0 in (3.35 m)
Wing area: 382 ft² (35.5 m²)
Empty weight: 1,220 lb (555 kg)
Loaded weight: 2,050 lb (930 kg)
Powerplant: 1× Gnome Monosoupape 9-cylinder rotary engine, 100 hp (75 kW)
Performance
Maximum speed: 70 mph (61 knots, 113 km/h) at 5,000 ft (1,520 m)
Range: 250 mi (217 NM, 403 km)
Service ceiling: 9,000 ft (2,743 m)
Wing loading: 5.4 lb/ft² (26 kg/m²)
Power/mass: 0.05 hp/lb (0.08 kW/kg)
Endurance 4 hours 30 minutes [9]
Climb to 5,000 ft (1,520 m): 16 min
Armament
1 × 0.303 in (7.7 mm) drum-fed Lewis gun in observer's cockpit
Airco DH.2
Role:Fighter
Manufacturer:Airco
Designed by:Geoffrey de Havilland
First flight:July 1915
Primary user:Royal Flying Corps
Number built:453
Developed from:Airco DH.1
General characteristics
Crew: 1
Length: 25 ft 2½ in (7.69 m)
Wingspan: 28 ft 3 in (8.61 m)
Height: 9 ft 6½ in (2.91 m)
Wing area: 249 ft² (23.13 m²)
Empty weight: 942 lb (428 kg)
Max takeoff weight: 1,441 lb (654 kg)
Powerplant: 1× Gnome Monosoupape rotary engine, 100 hp (75 kW)
Performance
Maximum speed: 93 mph (150 km/h) at sea level
Range: 250 mi (400 km)
Service ceiling: 14,000 ft (4,265 m)
Rate of climb: 545 ft/min (166 m/min)
Wing loading: 5.79 lb/ft² (28.3 kg/m²)
Power/mass: 0.069 hp/lb (110 W/kg)
Endurance 2¾ hours
Climb to 5,000 ft (1,500 m) 24 minutes 45 seconds
Armament
1 × .303 in (7.7 mm) Lewis gun using 47-round drum magazines
Manufacturer:Airco
Designed by:Geoffrey de Havilland
First flight:July 1915
Primary user:Royal Flying Corps
Number built:453
Developed from:Airco DH.1
General characteristics
Crew: 1
Length: 25 ft 2½ in (7.69 m)
Wingspan: 28 ft 3 in (8.61 m)
Height: 9 ft 6½ in (2.91 m)
Wing area: 249 ft² (23.13 m²)
Empty weight: 942 lb (428 kg)
Max takeoff weight: 1,441 lb (654 kg)
Powerplant: 1× Gnome Monosoupape rotary engine, 100 hp (75 kW)
Performance
Maximum speed: 93 mph (150 km/h) at sea level
Range: 250 mi (400 km)
Service ceiling: 14,000 ft (4,265 m)
Rate of climb: 545 ft/min (166 m/min)
Wing loading: 5.79 lb/ft² (28.3 kg/m²)
Power/mass: 0.069 hp/lb (110 W/kg)
Endurance 2¾ hours
Climb to 5,000 ft (1,500 m) 24 minutes 45 seconds
Armament
1 × .303 in (7.7 mm) Lewis gun using 47-round drum magazines
Monday, July 5, 2010
Fairchild Republic A-10 Thunderbolt II
An A-10 from the 81st Fighter Squadron, Spangdahlem Air Base, Germany was a ground-attack aircraft manufactured by Fairchild-Republic
First flight : 10 May 1972
Introduced : March 1977
Status : In service
Primary user : United States Air Force
Number built : 716
Unit cost : US$11.8 million (average, 1994 dollars)
General characteristics
Crew: 1
Length: 53 ft 4 in (16.26 m)
Wingspan: 57 ft 6 in (17.53 m)
Height: 14 ft 8 in (4.47 m)
Wing area: 506 ft² (47.0 m²)
Empty weight: 24,959 lb (11,321 kg)
Loaded weight: 30,384 lb (13,782 kg)
On CAS mission: 47,094 lb (21,361 kg)
On anti-armor mission: 42,071 lb (19,083 kg)
Max takeoff weight: 50,000 lb (23,000 kg)
Powerplant: 2× General Electric TF34-GE-100A turbofans, 9,065 lbf (40.32 kN) each
Performance
Never exceed speed: 450 knots (518 mph, 833 km/h) at 5,000 ft (1,500 m) with 18 Mk 82 bombs
Maximum speed: 381 knots (439 mph, 706 km/h) at sea level, clean
Cruise speed: 300 knots (340 mph, 560 km/h)
Stall speed: 120 knots (138 mph, 220 km/h)
Combat radius:
On CAS mission: 250 nmi (288 mi, 460 km) at 1.88 hour single-engine loiter at 5,000 ft (1,500 m), 10 min combat
On anti-armor mission: 252 nmi (290 mi, 467 km), 40 nm (45 mi, 75 km) sea-level penetration and exit, 30 min combat
Ferry range: 2,240 nmi (2,580 mi, 4,150 km) with 50 knot (55 mph, 90 km/h) headwinds, 20 minutes reserve
Service ceiling: 45,000 ft (13,700 m)
Rate of climb: 6,000 ft/min (30 m/s)
Wing loading: 99 lb/ft² (482 kg/m²)
Thrust/weight: 0.3
First flight : 10 May 1972
Introduced : March 1977
Status : In service
Primary user : United States Air Force
Number built : 716
Unit cost : US$11.8 million (average, 1994 dollars)
General characteristics
Crew: 1
Length: 53 ft 4 in (16.26 m)
Wingspan: 57 ft 6 in (17.53 m)
Height: 14 ft 8 in (4.47 m)
Wing area: 506 ft² (47.0 m²)
Empty weight: 24,959 lb (11,321 kg)
Loaded weight: 30,384 lb (13,782 kg)
On CAS mission: 47,094 lb (21,361 kg)
On anti-armor mission: 42,071 lb (19,083 kg)
Max takeoff weight: 50,000 lb (23,000 kg)
Powerplant: 2× General Electric TF34-GE-100A turbofans, 9,065 lbf (40.32 kN) each
Performance
Never exceed speed: 450 knots (518 mph, 833 km/h) at 5,000 ft (1,500 m) with 18 Mk 82 bombs
Maximum speed: 381 knots (439 mph, 706 km/h) at sea level, clean
Cruise speed: 300 knots (340 mph, 560 km/h)
Stall speed: 120 knots (138 mph, 220 km/h)
Combat radius:
On CAS mission: 250 nmi (288 mi, 460 km) at 1.88 hour single-engine loiter at 5,000 ft (1,500 m), 10 min combat
On anti-armor mission: 252 nmi (290 mi, 467 km), 40 nm (45 mi, 75 km) sea-level penetration and exit, 30 min combat
Ferry range: 2,240 nmi (2,580 mi, 4,150 km) with 50 knot (55 mph, 90 km/h) headwinds, 20 minutes reserve
Service ceiling: 45,000 ft (13,700 m)
Rate of climb: 6,000 ft/min (30 m/s)
Wing loading: 99 lb/ft² (482 kg/m²)
Thrust/weight: 0.3
Saturday, July 3, 2010
WRIGHT FLYER 1
With a length of 21 ft 1 inch (6.43 m) and a wingspan of 40 ft 4 inches, (12.29 m) the Flyer-1 can accommodate a crew of one person. Having an empty weight of 605 lb (274 kg) the maximum takeoff weight was only 745 lb (338 kg). Likewise, the performance of the aircraft was also limited. The maximum speed was only 30 mph (48 km/h), with a service ceiling of 30ft. The wing loading was only 1.4 lb/ft² (7 kg/m²) The Power/mass is 0.02 hp/lb (30 W/kg).
(F-100D)
F-1ooD is an aircraftof 50 ft (15.2 m) length and a wingspan of 38 ft 9 in (11.81 m) .It has a height of 16 ft 2¾ in (4.95 m) and a wing area of 400 ft² (37 m²) . Its mpty weight comes upto 21,000 lb (9,500 kg) and fully loaded weightcan be upto 28,847 lb (13,085 kg) . Its maximum take off weight is 34,832 lb (15,800 kg)
Maximum speed: 750 kn (864 mph, 1,390 km/h)
Range: 1,733 NM (1,995 mi, 3,210 km)
Service ceiling: 50,000 ft (15,000 m)
Rate of climb: 22,400 ft/min (114 m/s)
Wing loading: 72.1 lb/ft² (352 kg/m²)
Thrust/weight: 0.55
Lift-to-drag ratio: 13.9
Maximum speed: 750 kn (864 mph, 1,390 km/h)
Range: 1,733 NM (1,995 mi, 3,210 km)
Service ceiling: 50,000 ft (15,000 m)
Rate of climb: 22,400 ft/min (114 m/s)
Wing loading: 72.1 lb/ft² (352 kg/m²)
Thrust/weight: 0.55
Lift-to-drag ratio: 13.9
avion III
This ancient, one pilot aircraft has a wingspan of 16 m (52 ft 6 in) and a wing area: 56 m² (602 ft²) .Its loaded weight is 400 kg (880 lb)
Powerplant: 2× Ader alcohol-burning steam engines, 15 kW (20 hp) each
Wing loading: 7 kg/m² (1.5 lb/ft²)
Power/mass: 0.08 kW/kg (0.05 hp/lb)
Powerplant: 2× Ader alcohol-burning steam engines, 15 kW (20 hp) each
Wing loading: 7 kg/m² (1.5 lb/ft²)
Power/mass: 0.08 kW/kg (0.05 hp/lb)
Thursday, July 1, 2010
stealth B2 Spirit
The B2 Spirit is a US stealth bomber manufactured by Northrop Corporation and Northrop Grumman. It was used for the first time by US Air force on the17th of July 1789. The engines(4*General Electric F118-GE-100 non-after burning turbofans, 17,300lbf) of this a/c are placed in its wings. It can accommodate a crew of 2 members viz. the pilot and the mission commander. The B2 spirit is 69ft long and has a wingspan of 172ft while a height of 17ft and has 5140sqft wing area. It has a cruise speed of Mach 0.85 but can go up to a maximum speed of Mach 0.95. It has a range of 6000nmi and its service ceiling is 50,000ft.
Wing loading: 67.3lb/sq ft
Thrust/Weight: 0.205
Wing loading: 67.3lb/sq ft
Thrust/Weight: 0.205
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