Armstrong Whitworth Atlas Aircraft
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Production Details | |
Design Company: |
|
First Flight: |
10 May 1925 |
Atlas Prototype: |
1 - Sir W.G. Armstrong Whitworth Aircraft Ltd |
Atlas I: |
460 - Sir W.G. Armstrong Whitworth Aircraft Ltd |
Atlas II: |
17 - Sir W.G. Armstrong Whitworth Aircraft Ltd |
Type Specification | |
Applies to: |
Armstrong Whitworth Atlas I |
Type: |
Two seat Army co-operation biplane |
Wing: |
Single bay biplane. Wings are swept at 6 degrees. Lower wing is shorter than upper and is attached at the base of the fuselage. Upper wing is supported on a cabane of steel tubes in the form of a W. Wing structure is of corrugated steel strip covered in fabric. Balanced ailerons on upper wings only |
Fuselage: |
Fuselage structure on steel tube. Sides and bottom of fuselage are faired by formers and stringers, while the top decking consists of a wooden fairing around the cockpits |
Tail Unit: |
Tailplane mounted at top of fuselage of cantilever design. Balanced elevator and balanced rudder |
Landing Gear: |
Cross axle type. Axle carried on Vees. Tail skid |
Power Plant: |
One 400 hp Jaguar IVC |
Accommodation: |
Pilot seated in forward cockpit, observer behind |
Dimensions | |
Span: |
39 ft 7 in |
Length: |
28 ft 7 in |
Height: |
10 ft 6 in |
Wing Area: |
391 sq ft |
Weights | |
Empty: |
2,550 lb |
Max: |
4,020 lb |
Performance | |
Max Speed: |
142 mph at sea level |
Climb: |
28 min to 15,000 ft |
Service Ceiling: |
16,800 ft |
Endurance: |
3.25 hr |
Preserved in British Museums | |
None known | |
Web Sites | |
http://www.rcaf.com/aircraft/fighters/atlas/index.php?name=atlas |