Northrop X-21
From Biocrawler, the free encyclopedia.
The Northrop X-21 was an experimental aircraft designed to test wings with laminar flow control. It was based on the Douglas WB-66D airframe, with the wing-mounted engines moved to the rear fuselage and making space for air compressors.
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Specifications (X-21A)
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General Characteristics
- Crew:
- Length: 75 ft 3 in (22.94 m)
- Span: 93 ft 6 in (28.51 m)
- Height: ft in ( m)
- Wing area: ft² ( m²)
- Empty: lb ( kg)
- Loaded: 83,000 lb (37,727 kg)
- Maximum takeoff: lb ( kg)
- Powerplant: 2x General Electric J79-GE-13, 9,400 lbf (41.9 kN) thrust each
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Performance
- Maximum speed: 560 mph (896 km/h)
- Range: miles ( km)
- Service ceiling: 42,500 ft (12,957 m)
- Rate of climb: ft/min ( m/min)
- Wing loading: lb/ft² ( kg/m²)
- Power/Mass: hp/lb ( kW/kg)
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Related content
Related development: B-66 Destroyer
Comparable aircraft:
Designation sequence: X-18 - X-19 - X-20 - X-21 - X-22 - X-23 - X-24
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