Armstrong Siddeley Tiger (radial)

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. First run in 1932, 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.

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

Specifications:

Tiger VIII
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)
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
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)