The Lutetia 4.C.02 was a small V-4 two-stroke engine designed soon after World War II and intended to power light aircraft.
| Lutetia 4.C.02 | |
|---|---|
| Type | Air-cooled, 90° V-4 two-stroke engine |
| National origin | France |
| Manufacturer | Moteurs Lutetia |
| Designer | Marcel Echard |
| First run | c.1950 |
Design and development
editMarcel Echard was an engine designer with a lifetime interest in two-strokes. His first such engine was built in 1911 and he began work on the 4.C.02 in 1949. By 1953 this engine had achieved its homologation and had been test-flown on a Jodel D.9.[1] The Briffaud GB-6 is the only known application, a one-off aircraft with a short life, though not because of its engine.[2]
Unusually for a two-stroke, the fuel/air mixture was compressed externally rather than in the crankcase.[1]
Applications
editSpecifications
editData from Jane's All the World's Aircraft 1953-54[1]
General characteristics
- Type: air-cooled, 90° V-4 two-stroke engine
- Bore: 76 mm (3.0 in)
- Stroke: 70 mm (2.8 in)
- Displacement: 1.267 L (77.32 cu in)
- Length: 647.5 mm (25.49 in)
- Width: 494 mm (19.4 in)
- Height: 518 mm (20.4 in)
- Dry weight: 46 kg (101 lb)
Components
- Fuel system: standard carburettor followed by compressor injection into cylinders; no crankcase compression.
- Oil system: pressure fed from finned sump by internal pump
- Cooling system: air; heads cast in finned pairs
- Ignition system: twin magnetos, two plugs/cylinder
Performance
- Power output: take-off and maximum continuous, 33 kW (44 hp) at 2,800 rpm; cruise, 23 kW (31 hp) at 2,500 rpm; cruise
- Compression ratio: 7.2
- Fuel consumption: 377 gm/kW/hr (0.535 lb/hp/hr)