Walter Sagitta
Appearance
(Redirected from Walter Sagitta I-MR)
Sagitta | |
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Type | Piston aero engine |
National origin | Czechoslovakia |
Manufacturer | Walter Aircraft Engines |
First run | 1937 |
The Walter Sagitta was a Czechoslovakian, air-cooled, inverted V-12 engine that first ran in 1937. This was one of several smaller, low-mass medium power pre-war V-12 engines produced. With a displacement of 18.4 liters (1,123 cu in), it produced up to 373 kW (550 hp) at 2,500 rpm.[1]
Variants
- Sagitta I-MR
- 410 kW (550 hp) at 2,500rpm at 2,500 m (8,200 ft) - rated height[2]
- Sagitta I-SR
- 400 kW (535 hp) at 2,500rpm at 3,800 m (12,500 ft) - rated height[2]
- Sagitta II R.C.
- 388 kW (520 hp), fully supercharged.[3]
- Alfa Romeo 122
- Licensed production.
Applications
Specifications (Sagitta I-MR)
![](http://upload.wikimedia.org/wikipedia/commons/thumb/2/2b/Walter_Sagitta_I-SR_%281939%29_2.jpg/220px-Walter_Sagitta_I-SR_%281939%29_2.jpg)
Data from Jane's.[2]
General characteristics
- Type: 12-cylinder inverted vee piston engine
- Bore: 118 mm (4.65 in)
- Stroke: 140 mm (5.51 in)
- Displacement: 18.372 L (1,121.1 cu in)
- Length: 1,914 mm (75.35 in)
- Width: 725 mm (28.54 in)
- Height: 796 mm (31.34 in)
- Dry weight: 372 kg (820 lb)
Components
- Valvetrain: Enclosed push-rod operated rockers, two valves per cylinder closed by triple springs
- Supercharger: 8.7 times crankshaft speed
- Fuel system: Automatic boost and mixture control by a horizontal carburettor
- Fuel type: 85 Octane petrol
- Oil system: Dry sump, one pressure pump and two scavenge pumps
- Cooling system: Air-cooled
Performance
- Power output:
- Take-off: 418 kW (560 hp) at 2,500 rpm
- Rated power: 410 kW (550 hp) at 2,500 rpm at 2,300 m (7,500 ft)
- Maximum power: 447 kW (600 hp) at 2,500 rpm at 1,750 m (5,740 ft)
- Specific power: 24.29 kW/L (0.534 hp/(cu in))
- Compression ratio: 6.25:1
- Specific fuel consumption: 0.315 - 0.328 kg/(kW h) (0.525 - 0.548 lb/(hp h))
- Oil consumption: 0.004 - 0.0067 kg/(kW h) (0.0067 - 0.11 lb/(hp h))
- Power-to-weight ratio: 1.046 kW/kg (0.636 hp/lb)
See also
Comparable engines
Related lists
References
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- Notes
- Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9