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Gnome-Rhône 14M

From Wikipedia, the free encyclopedia

Gnome-Rhône 14M Mars
Gnome Rhone M05 Mars.JPG
A preserved Gnome-Rhône 14M-05 Mars
Type Radial engine
National origin France
Manufacturer Gnome et Rhône
First run 1936
Developed from Gnome-Rhône 14N

The Gnome-Rhône 14M was a small 14-cylinder two-row air-cooled radial engine that was used on several French and German aircraft of World War II. While having the same appearance, number of pistons (14) and two-row layout typical of Gnome-Rhône radial engines, the 14M was built to a smaller frame intended to power a lighter class of aircraft. It was designed with lower displacement and power, smaller in size and with less weight compared to the larger, heavier Gnome-Rhône 14N and its well-known predecessor.

Variants

14M-00
LH rotation, 474 kW (635 hp)
14M-01
RH rotation identical to 14M-00
14M-04
LH rotation, 521.99 kW (700 hp)
14M-05
RH rotation identical to 14M-04
14M-06
LH rotation, 521.99 kW (700 hp), reduction gear 0.71:1
14M-07
RH rotation identical to 14M-06
14M-08
LH rotation, 559.27 kW (750 hp), reduction gear 0.71:1
14M-09
RH rotation identical to 14M-08

Applications

Specifications (14M-4)

(14M-5 identical except opposite rotation)

Data from [1]

General characteristics

  • Type: Fourteen-cylinder two-row supercharged air-cooled radial engine
  • Bore: 122 mm (4.80 in)
  • Stroke: 116 mm (4.57 in)
  • Displacement: 18.92 L (1,154.6 cu in)
  • Length: 1,251 mm (49.25 in)
  • Diameter: 950 mm (37.40 in)
  • Dry weight: 419 kg (924 lb)

Components

Performance

  • Power output:
  • (Take-off): 521.99 kW (700 hp) at 3,030 rpm for takeoff with 1,100 mm (43.3 in) Hg / +3 kg (6.6 lb) boost
  • (Normal): 492.16 kW (660 hp) at 3,030 rpm at 4,000 m (13,123 ft)
  • (cruising): 339.29 kW (455 hp) at 2,350 rpm at 4,000 m (13,123 ft)
  • Specific power: 27.21 kW/l (0.61 hp/(cu in))
  • Compression ratio: 6.5:1
  • Specific fuel consumption: 0.29 kg/(kW h) (0.48 lb/(hp h))
  • Oil consumption: 0.01 kg/(kW h) (0.018 lb/(hp h))
  • Power-to-weight ratio: 1.27 kW/kg (0.77 hp/lb)

See also

References

  1. ^ Wilkinson, Paul H. (1946). Aircraft Engines of the World. London: Sir isaac Pitman & Sons Ltd.
This page was last edited on 16 January 2021, at 19:37
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