British Aircraft Corporation BAC.221

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Contents

Type Description

• Type 221
• A single-seat research aircraft, the Type 221 was a modified Fairey F.D.2 to test the "ogee delta" wing design to be used on the BAC Concorde. The contract had originally been awarded to Fairey for a modified F.D.2 to Specification ER.196D, but following Fairey's absorbtion into Westland, the work was transferred to Hunting, but eventually, as part of BAC's redistribution of work to Filton, Bristol took over the project under Specification ER.221D.
  The Type 221 featured a new wing of slender ogival delta planforrn with aspect ratio 1.22, thickness/chord ratio 4.5%, sweepback on the leading-edge over main portion of each wing 65°, curving round to streamwise tip. A sharp leading-edge extended forward along each side of fuselage to maintain vortex attachment. The all-metal three-spar box structure formed an integral fuel tank. The entire trailing-edge of each wing was made up of an aileron, outboard, and an elevator inboard, of conventional all-metal construction. Engine intakes were relocated under the foreward leading edge. Other than a a six foot extension, the fuselage was essentially that of the F.D.2, an all-metal semiomonocoque structure that retained the F.D.2’s drooping nose, which could be lowered hydraulically by 10°, but intermediate angles of 5° and 8° were added. Four petal ainbrakes around jet nozzle. The sweptback fin and rudder, of conventional metal construction, was modified from that of the F.D.2.
  A lengthened undercarriage was fitted, to mimic Concorde's attitude on the ground. The rearward-retracting twin-wheell nose unit utilised a modified Fairey Gannct shock-absorber and Lightning-type shimmy damper. The single-wheel Dowty-Rotol main units were based on those of the Lightning and retract forward, turning through 90° so that wheels stowed horizontally in the wings. A brake parachute was stowed in fairing below rudder. In the first part of 1965, a major modification programme was implemented. The metal canopy from the FD2 was replaced by a frangible Plexiglas canopy, safer in case of pilot ejection; the cockpit interior was altered and the tail fin extended by 8in. One 14,000 lb.s.t. Rolls-Royce Avon RA.28R powerplant.

Specification
Span	Length	Height	Wing Area	Empty Wt	Max AUW	Cruise Speed	Maximum Speed	Range	Service Ceiling
25 ft	57 ft 8 in	11 ft 4 in	490 sq ft		13884 lb		1061 mph/ 922 kn
7.62 m	17.58 m	3.45 m	45.52 m2		6298 kg		1708 kph

Production Details

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Production Summary

Production References

1. British Experimental Turbojet Aircraft, Barry Jones (The Crowood Press, 2003)
2. British Experimental Jet Aircraft, Barrie Hygate (Argus Books, 1990)
3. Ministry of Aircraft Production Aeroplane Price Books (Dept of Archive and Aviation Records, RAF Museum, Hendon, Records X005-2126)