Napier Dagger
| Dagger | |
|---|---|
| |
| Napier Dagger at the National Air and Space Museum | |
| Type | Piston aero-engine |
| Manufacturer | Napier & Son
|
| First run | 1934 |
| Major applications | Handley Page Hereford
Hawker Hector |
The Napier Dagger was a 24-cylinder
Napier before World War II. It was a development of the earlier Napier Rapier
.
Design and development
The H-Block has a compact layout, as it essentially consists of two vertically opposed, flat-twelve
rpm but unlike the later Napier Sabre, it had conventional poppet valves
.
Although considered a masterpiece of engine design by
Handley Page Hereford, a variant of the Hampden bomber. The operational usefulness of the Hector was restricted by engine cooling problems, which made it unsuitable for operations in the tropics and the Hereford was found to be unsuitable for combat, because its Dagger VIII engines were noisy and unreliable. The Dagger was also used in the experimental Martin-Baker MB 2
fighter.
Variants
- Napier-Halford Dagger I
1934 – 650 hp.
- Dagger II
1938 – 755 hp
- Dagger IIIM
1938 – 725 hp
- Dagger VIII
1938 – 1000 hp, intermediate altitude supercharger, initially known as E.108[1]
Applications
Some of these aircraft were test beds only.
- Fairey Battle testbed only
- Handley Page Hereford - a few aircraft used for training only[2]
- Hawker Hart
- Hawker Hector
- Martin-Baker MB 2 - single private venture prototype
Engines on display
A preserved Napier Dagger is on display at the Royal Air Force Museum London.
Specifications (Napier Dagger III MS)
Data from Lumsden[3]
General characteristics
- Type: Twenty-four-cylinder supercharged air-cooled H engine
- Bore: 3.813 in (96.8 mm)
- Stroke: 3.75 in (95.25 mm)
- Displacement: 1,027 in³ (16.8 L)
- Length: 80 in (2,032 mm)
- Width: 22.5 in (584 mm)
- Height: 45.125 in (1,146 mm)
- Dry weight: 1,358 lb (616 kg)
Components
- Valvetrain: One inlet and one exhaust valve per cylinder
- centrifugal type supercharger, 5.04:1 reduction
- Fuel system: Napier-Claudel-Hobson carburettor
- Fuel type: 87 Octane petrol
- Cooling system: Air-cooled
- Reduction gear: Spur, 2.69:1
Performance
- Power output: * 725 hp (541 kW) at 3,500 rpm for takeoff
- 794 hp (592 kW) at 4,000 rpm at 5,000 ft (1,520 m)
- Specific power: 0.77 hp/in³ (35.13 kW/L)
- Compression ratio: 7.75:1
- Specific fuel consumption: 0.43 lb/(hp•h) (261 g/(kW•h))
- Oil consumption: 0.18–0.35 oz/(hp•h) (7–13 g/(kW•h))
- Power-to-weight ratio: 0.62 hp/lb (1.02 kW/kg)
See also
Related development
Comparable engines
Related lists
References
- Jane's All the World's Aircraft 1942
Notes
Bibliography
- "Britain's Aero Engines". archive at flightglobal.com. 3 November 1938.
- Gunston, Bill. World Encyclopedia of Aero Engines: From the Pioneers to the Present Day. 5th edition, Stroud, UK: Sutton, 2006. ISBN 0-7509-4479-X
- Lumsden, Alec. British Piston Engines and Their Aircraft. Marlborough, UK: Airlife Publishing, 2003. ISBN 1-85310-294-6.
- White, Graham. Allied Aircraft Piston Engines of World War II: History and Development of Frontline Aircraft Piston Engines Produced by Great Britain and the United States During World War II. Warrendale, Pennsylvania: SAE International, 1995. ISBN 1-56091-655-9
External links
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