Northrop X-21A

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Northrop X-21A
Northrop X-21A
Type	experimental aircraft
Manufacturer	Northrop
Maiden flight	18 April 1963
Retired	1968
Primary user	National Aeronautics and Space Administration (NASA)
Number built	2

The Northrop X-21A 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. The aircraft first flew on 18 April 1963 with NASA test pilot Jack Wells at the controls.^[1] Although useful testing was accomplished, the extensive maintenance of the intricate laminar-flow system caused the end of the program.

Contents 1 Design and development 2 Testing 3 Surviors 4 Specifications (X-21A) 4.1 General characteristics 4.2 Performance 5 References 6 External links 7 Related content 8 Reference

[edit] Design and development

Laminar-flow control is a technology that offers the potential for significant improvement in drag coefficient which would provide improvements in aircraft fuel usage, range or endurance that far exceed any known single aeronautical technology. In principle, if 80% of wing is laminar, then overall drag could be reduced by 25%. The frictional force between the air and the aircraft surface, known as viscous drag, is much larger in a turbulent boundary layer than in a laminar one. The principal type of active laminar-flow control is removal of a small amount of the boundary-layer air by suction through porous materials, multiple narrow surface slots, or small perforations.

Two major modifications were required, the first involving the standard underwing podded J71 engines being removed and replaced by a pair of 9490 lb.s.t General Electric XJ79-GE-13 non-afterburning turbojets mounted in pods attached to the rear of the fuselage sides. Bleed air from the J79 engines was fed into a pair of underwing fairings, each of which housed a "bleed-burn" turbine which sucked the boundary layer air out through the wing slots.

The X-21A test vehicles (55-0408 and 55-0410) also incorporated sophisticated laminar flow control systems built into a completely new wing of increased span and area, with a sweep reduced from 35 ° to 30 °. The wing had a multiple series of span-wise slots (800,000 in total ^[2]) through which turbulent boundary-layer was "sucked in," resulting in a smoother laminar flow. Theoretically, reduced drag, better fuel economy and longer range could be achieved. ^[3]

The forward cockpit carried a pilot and two flight engineers while two additional flight test engineers were housed in a central fuselage bay underneath the wing.

[edit] Testing

In initial testing there were significant problems with the porous materials and surface slots getting plugged with debris, bugs, even rain. In certain conditions, ice crystals would form due to the rapid cooling of air over those laminar surfaces abruptly disrupting laminar flow, causing rapid melting and rapid transition back to laminar flow. Maximum achievement was 95% laminar flow over those areas desired^[4]. However, the design effort was cancelled due to the plugging problems.

Nevertheless, pioneering data were obtained in the X-21 flight program, including the effects of surface irregularities, boundary-layer turbulence induced by three-dimensional spanwise flow effects in the boundary layer (referred to as spanwise contamination) and degrading environmental effects such as ice crystals in the atmosphere.^[5]

[edit] Surviors

Both X-21As ended up in storage at Edwards Air Force Base, California where gradually, they became derelicts. The remains can still be viewed but no efforts have been made to recover a single example for restoration or display. ^[6]

[edit] Specifications (X-21A)

[edit] General characteristics

• Crew:5
• Length: 75 ft 3 in (22.94 m)
• Span: 93 ft 6 in (28.51 m)
• Height: 25 ft 7 in ( 7.8 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

[edit] 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)

[edit] References

• Baugher,Joe. Northrop X-21A. [3] Access date: 14 February 2007.
• "Northrop X-21A." X-Planes Detailed Data. [4] Access date: 14 February 2007.
• Winchester, Jim. X-Planes and Prototypes. London: Amber Books Ltd., 2005. ISBN 1-904687-40-7.

[edit] External links

• [history.nasa.gov/monograph39/mon39_a.pdf "Laminar-flow Control: The Holy Grail of Aerodynamics." Innovation in Flight.]

[edit] 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

[edit] Reference

1. ^ American X-Vehicles: An Inventory. Access date: 13 February 2007.
2. ^ Winchester 2005, p. 297.
3. ^ Baugher,Joe. Northrop X-21A. [1] Access date: 14 February 2007.
4. ^ Winchester 2005, p. 297.
5. ^ [history.nasa.gov/monograph39/mon39_a.pdf]
6. ^ Winchester 2005, p. 297.