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

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.

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

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

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

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)