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

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.

Design and development

Marcel 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

Specifications

Data from Jane's All the World's Aircraft 1953-54[1]

General characteristics

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)

References

  1. 1 2 3 Bridgman, Leonard (1953). Jane's All the World's Aircraft 1953-54. London: Sampson, Low, Marston and Co. Ltd. p. 327.
  2. ↑ Gaillard, Pierre (1990). Les Avions Francais de 1944 a 1964 (in French). Paris: Editions EPA. p. 158. ISBN 2 85120 350 9.
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.