Armstrong Whitworth Awana
|Role||Military transport biplane|
|First flight||28 June 1923|
Design and development
The Awana was designed in response to Air Ministry Specification 5/20 for a twin-engined Troop Carrying Aeroplane, able to carry 25 fully equipped troops for a distance of 400 miles. Any design was to be capable of landing on rough terrain, other requirements being folding wings and the ability to fly on one engine.
One of the largest landplanes of its time, it was a large, twin-engine four-bay staggered biplane with a box-like fuselage, and a three-rudder, biplane tail. The pilot and navigator sat in open cockpits atop the nose, while the 25 troops it was to carry entered through a hatch in the floor and sat in two rows of "bus"-style seats with a centre aisle. It was of composite construction, with a tubular-steel-framed fuselage and wooden wings incorporating substantial hinges to allow them to be folded for storage. The Napier Lion engines were supported on tubular-steel supports between the wings and housed in streamlined cowlings with retractable radiators on the underside. The three cylindrical main petrol tanks were slung under the floor in an aluminium fairing, and fed fuel via windmill-driven pumps to header tanks on the underside of the upper wing.
Two prototypes were ordered by the Air Ministry on 27 June 1921, and the first prototype, serial number J6897, first flew on 28 June 1923. Evaluated at Martlesham Heath, control during landing was found to be poor, and the structure overall too flimsy. The second prototype addressed some of these concerns, but the Vickers Victoria was selected for production instead.
Data from Armstrong Whitworth Aircraft since 1913 
- Crew: two, pilot and navigator
- Capacity: 25 troops
- Length: 68 ft 0 in (20.73 m)
- Wingspan: 105 ft 6 in (32.16 m)
- Height: 20 ft 3 in (6.17 m)
- Wing area: 2,300 ft² (213.7 m²)
- Empty weight: 10,000 lb (4,536 kg)
- Loaded weight: 18,450 lb (8,369 kg)
- Powerplant: 2 × Napier Lion 12-cylinder W-block inline engine, 450 hp (335 kw) each
- Maximum speed: 84 kn (97 mph, 156 km/h) at 1,000 ft (305 m)
- Range: 313 nmi (360 mi, 580 km)
- Service ceiling: 8,000 ft (2,440 m)
- Rate of climb: 300 ft/min (1.5 m/s)
- Climb to 5,000 ft (1,520 m): 19.7 min
Aircraft of comparable role, configuration and era
|Wikimedia Commons has media related to Armstrong Whitworth Awana.|
- Meekcoms/Morgan 1994, p. 35
- Flight 3 April 1924 page 187
- Flight 3 April 1924 page187 et seq
- Topper 1988, p.192.
- Tapper 1988, p.208.
- Tapper 1988, p.190.
- Meekcoms, K J; Morgan, E B (1994). The British Aircraft Specification File. Tonbridge, Kent, England: Air-Britain. ISBN 0 85130 220 3.
- Tapper, Oliver (1989). Armstrong Whitworth Aircraft since 1913. London: Putnam. ISBN 0-85177-826-7.
- Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. p. 79.
- World Aircraft Information Files. London: Bright Star Publishing. pp. File 889 Sheet 80.