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.

Specifications (X-21A)

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

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)

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