| Tiger | |
|---|---|
| |
| Armstrong Siddeley Tiger at the Science Museum (London) | |
| Type | Radial engine |
| Manufacturer | Armstrong Siddeley |
| First run | 1932 |
| Major applications | Armstrong Whitworth Ensign Blackburn Shark |
The Armstrong Siddeley Tiger was a British 14-cylinder air-cooled aircraft radial engine developed by Armstrong Siddeley in the 1930s from their Jaguar engine. The engine was built in a number of different versions but performance and dimensions stayed relatively unchanged. The Tiger VIII was the first British aircraft engine to use a two-speed supercharger.[1][2]
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Transcription
Applications
- Armstrong Whitworth A.W.19
- Armstrong Whitworth AW.23
- Armstrong Whitworth A.W.29
- Armstrong Whitworth Ensign
- Armstrong Whitworth Whitley
- Blackburn B-6
- Blackburn B-7
- Blackburn Shark
- Blackburn Ripon
- Fairey G4/31
- Handley Page H.P.51
- Short Calcutta
Engines on display
A preserved Armstrong Siddeley Tiger is on display at the Science Museum (London).
Specifications (Tiger VIII)
Data from Lumsden.[3]
General characteristics
- Type: 14-cylinder supercharged two-row air-cooled radial engine
- Bore: 5.5 in (139.7 mm)
- Stroke: 6.0 in (152.4 mm)
- Displacement: 1,995 in³ (32.7 L)
- Length: 64.6 in (1,641 mm)
- Diameter: 50.8 in (1,290 mm)
- Dry weight: 1,287 lb (584 kg)
Components
- Valvetrain: Two pushrod-actuated valves per cylinder
- Supercharger: Two-speed centrifugal type supercharger, first gear ratio 5.34:1, second gear 7.96:1.
- Fuel system: Claudel-Hobson carburettor
- Fuel type: 87 octane rating petrol
- Cooling system: Air-cooled
- Reduction gear: Spur, 0.594:1
Performance
- Power output:
- 907 hp (677 kW) at 2,375 rpm for takeoff
- 850 hp (634 kW) at 2,450 rpm at 7,150 ft (2,180 m) – first supercharger gear
- 771 hp (575 kW) at 2,450 rpm at 16,240 ft (4,950 m) – second supercharger gear
- 582 hp (434 kW) at 2,200 rpm economy cruise
- Specific power: 0.45 hp/in³ (20.7 kW/L)
- Compression ratio: 6.25:1
- Specific fuel consumption: 0.49 lb/(hp•h) (294 g/(kW•h))
- Oil consumption: 0.21–0.42 oz/(hp•h) (8–16 g/(kW•h))
- Power-to-weight ratio: 0.70 hp/lb (1.16 kW/kg)
See also
Related development
Related lists
References
Notes
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Lumsden, Alec. British Piston Engines and their Aircraft. Marlborough, Wiltshire: Airlife Publishing, 2003. ISBN 1-85310-294-6.
External links
This page was last edited on 13 September 2022, at 23:32