Walter Mars I
| Mars I | |
|---|---|
| |
| Walter Mars I powered DAR 4 trimotor c.1930 | |
| Type | 9-cylinder radial engine |
| National origin | Czechoslovakia |
| Manufacturer | Walter Engines |
| First run | c.1929 |
The Walter Mars I was a nine-cylinder, air-cooled, radial engine for aircraft use built in Czechoslovakia in the late 1920s.
Design and development
The Mars I was the largest capacity design of a series of three similar radial engines developed by the Walter company. Common cylinders were used for the five-cylinder Walter Vega and the seven-cylinder Walter Venus, the Mars I being a nine-cylinder engine.[1]
Applications
Specifications
Data from Flight, July 1929.[1]
General characteristics
- Type: 9-cylinder radial engine
- Bore: 105 mm (5.90 in)
- Stroke: 120 mm (4.72 in)
- Displacement: 9.352 L (570.7 cu in)
- Dry weight: 159 kg (350 lb)
Components
- Fuel system: Zenith Type 42 carburettor; two plugs/cylinder and twin Scintilla magnetos
- Cooling system: Air-cooled
- Reduction gear: Direct drive
Performance
- Power output: 112 kW (150 hp)
- Compression ratio: 5.15:1
- Power-to-weight ratio: 0.72 kW/kg (0.43 hp/lb)
See also
Related lists
References
Wikimedia Commons has media related to Walter aircraft engines.
- ^ a b "Czechoslovakia". Flight. XXI: 762. 25 July 1929.