Grumman X-29

Specifications

1st Flight 1984

Crew: 1

Capacity: 4,000 lb (1,814 kg) payload

Length: 53 ft 11.25 in (16.4402 m) including nose probe

48 ft 1 in (15 m) fuselage only

Wingspan: 27 ft 2.5 in (8.293 m)

Height: 14 ft 3.5 in (4.356 m)

Wing area: 188.84 sq ft (17.544 m2)

Aspect ratio: 3.9

Airfoil: root: Grumman K MOD 2 (6.2%); tip: Grumman K MOD 2 (4.9%)

Empty weight: 13,800 lb (6,260 kg)

Max takeoff weight: 17,800 lb (8,074 kg)

Fuel capacity: 3,978 lb (1,804 kg) in two fuselage bladder tanks and two strake integral tanks

Powerplant: 1 × General Electric F404-GE-400 afterburning turbofan engine, 16,000 lbf (71 kN) with afterburner

Performance

Maximum speed: 956 kn (1,100 mph, 1,771 km/h) at 33,000 ft (10,058 m)

Maximum speed: Mach 1.8

Range: 350 nmi (400 mi, 650 km)

Service ceiling: 55,000 ft (17,000 m)

Avionics

Litton LR-80 AHRS

Magnavox AN/ARC-164 UHF

Teledyne RT-1063B/APX-101V IFF/SIF

Honeywell triple redundant fly-by-wire FCS

Variants

The Grumman X-29 was an American experimental aircraft that tested a forward-swept wing, canard control surfaces, and other novel aircraft technologies.

The X-29 was developed by Grumman, and the two built were flown by NASA and the United States Air Force.

The aerodynamic instability of the X-29’s airframe required the use of computerized fly-by-wire control.

Composite materials were used to control the aero-elastic divergent twisting experienced by forward-swept wings, and to reduce weight.

The aircraft first flew in 1984, and two X-29s were flight tested through 1991.

 

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