The Lockheed P-80 Shooting Star was a straight-winged jet fighter developed and produced by the American company Lockheed. Introduced in 1945, it was the first jet fighter operated by the United States Army Air Forces. The aircraft was built from 1945 until 1950 with a total number of 1,715 units produced and was retired with the United States in 1959.

Lockheed Martin Aeronautics
United States
1945 to: 1950
US$0.11 million (1945)
1x Allison J33-A-35
4,600 pound-force
Max Cruise Speed:
516 knots
956 Km/h
Approach Speed (Vref):
Travel range:
1,200 Nautical Miles
2,222 Kilometers
Fuel Economy:
Service Ceiling:
46,800 feet
Rate of Climb:
6870 feet / minute
34.90metre / second
Take Off Distance:
Landing Distance:
Max Take Off Weight:
7,257 Kg
15,999 lbs
Max Landing Weight:
6,350 Kg
13,999 lbs
Max Payload:
1,000 Kg
2,205 lbs
Fuel Tank Capacity:
885 gallon
3,350 litre
Baggage Volume:
Seats - Economy / General:
1 seats
Seats - Business Class:
Seats - First Class:
Cabin Height:
Cabin Width:
Cabin Length:
Exterior Length:
10.5 metre - 34.45 feet
Tail height:
3.45 metre - 11.32 feet
Fuselage Diameter:
1 metre - 3.28 feet
Wing Span / Rotor Diameter:
11.83 metre - 38.81 feet
Wing Tips:
No Winglets

Blog Mentions

Blog posts that mention the Lockheed P-80 Shooting Star:

On January 8, 1944, the aircraft prototype designated as XP-80 performed its maiden flight. It was powered by a single de Havilland-built Halford H.1B turbojet. The aircraft was designed with a conventional all-metal airframe and fitted with a thin and straight low wing, and a tricycle arrangement undercarriage.

In late 1944, it entered into service. The Shooting Star was the first fighter jet in operations with its engine located in the fuselage.  It was produced from 1945 to 1950 with a total number of 1,715 units built.

The single-seat P-80 has an external length of 10.49 meters, an external height of 10.5 meters, and a fuselage width of 1 meter. It has a tail height of 3.43 meters and a wheelbase of 3.6 meters. It featured a straight wing with a wingspan of 11.81 meters and a wing area of 22.07 square meters. The aircraft has an empty weight of 3,819 kg, a gross weight of 5,534 kg, and a maximum takeoff weight of 7,646 kg. The maximum payload is 1,000 kg and the fuel tank capacity is 885 US gal.

The P-80 Shooting Star is powered by a single Allison J33-A-35 engine. It is a centrifugal compressor turbojet with water injection, a single-stage double-sided centrifugal compressor, fourteen can type stainless steel combustion chambers, a single-stage axial turbine, and a wet sump oil system. The engine produces a 4,600 lbf dry thrust and 5,400 lbf with water injection. The aircraft has a maximum speed of 516 knots at sea level and a cruise speed of 381 knots. It has a standard range of 717 nautical miles and a ferry range of 1,200 nautical miles. It can fly up to 46,800 feet and can climb at a rate of 6,870 feet per minute.

The P-80 could be loaded with six 12.7 mm M3 Browning heavy machine guns, eight 127 mm HVAR (High-Velocity Aircraft Rocket) unguided rockets, and two 450 kg of bombs.





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