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Gnome et Rhône 14R 04-05 - Musée Safran 07.jpg
Type 14 cylinder two-row air-cooled radial piston engine
National origin France
Manufacturer Gnome-Rhône / SNECMA
Major applications Breguet Br 500 Colmar
Developed from Gnome-Rhône 14N

The SNECMA 14R was a 14-cylinder two-row air-cooled radial engine developed in France just prior to the start of World War II from the Gnome-Rhône 14N. The 14N radial engine was itself an improved version of the popular pre-war Gnome-Rhône 14K Mistral Major series; designed and manufactured by Gnome et Rhône, a major French aircraft engine manufacturer whose origins pre-date the First World War.

The improved 14R was initially known as the Gnome-Rhône 14R. With the Fall of France, engine development was stopped under the occupation. After the war, development recommenced; however production of this engine after 1945 was transferred to the newly formed SNECMA and the engine was renamed the SNECMA 14R.


Improved higher performance using 92 Octane fuel. 14N with 2-speed supercharge (6.5:1 and 9:1), LH rotation, 1,190 kW (1,590 hp) for take-off.
RH rotation version of 14R-4.
RPM increased from 2,400 to 2,600 improving power output. LH rotation.
RH rotation version of 14R-08
LH rotation, 1,200 kW (1,600 hp).
RH rotation version of 14R-24.
LH rotation, 1,200 kW (1,600 hp).
RH rotation version of 14R-26.
LH rotation, 1,200 kW (1,600 hp).
RH rotation version of 14R-28.
LH rotation
LH rotation
RH rotation
28 cylinder, double 14R-24 engines placed back-to-back with co-axial contra-rotating propeller shafts, direct fuel injection, 2-speed supercharger, 77.4 l (4,720 cu in) displacement, delivering 2,400 kW (3,200 hp) for take-off using 100/130 octane fuel.[1]

Specifications (14R-04)

Data from [2]

General characteristics

  • Type: 14 cylinder two-row air-cooled radial piston engine
  • Bore: 146 mm (5.75 in)
  • Stroke: 165 mm (6.50 in)
  • Displacement: 38.7 l (2,361.62 cu in)
  • Length: 1,635 mm (64.37 in)
  • Diameter: 1,297 mm (51.06 in)
  • Dry weight: 819 kg (1,805.59 lb)
  • Frontal Area: 1.33 m2 (14.3 sq ft)


  • Valvetrain: Single inlet and exhaust valves operated by rockers and pushrods
  • Supercharger: Gear-driven 2-speed supercharger at 6.5:1 and 9.0:1 ratios
  • Fuel system: 1x Bronzavia updraught carburettor with automatic boost and altitude control
  • Fuel type: 92 Octane gasoline
  • Oil system: Pressure fed at 480 kPa (70 psi)
  • Cooling system: Air-cooled with baffles
  • Reduction gear: Planetary / epicyclic bevel reduction gearing at 0.67:1 ratio
  • Starter: Air equipment electric inertia starter
  • Ignition: 2 x R.B. magnetos, 2 x 18 mm (0.71 in) short reach spark plugs per cylinder fed by a shielded ignition harness.


  • Power output:
  • Take-off:1,590 hp (1,185.66 kW) at 2,600 rpm at 1,180 mm (46.46 in) Hg boost with 100 octane fuel
    • Military, low:1,660 hp (1,237.86 kW) at 2,600 rpm at 1,000 m (3,280.84 ft)
    • Military, high:1,580 hp (1,178.21 kW) at 2,600 rpm at 5,500 m (18,044.62 ft)
    • Normal, low:1,320 hp (984.32 kW) at 2,400 rpm at 2,100 m (6,889.76 ft)
    • Normal, high:1,230 hp (917.21 kW) at 2,400 rpm at 6,000 m (19,685.04 ft)
  • Specific power: 31.85 kW/l (0.7 hp/
  • Compression ratio: 6.8:1
  • Specific fuel consumption: 0.292 kg/kW/hr (0.48 lb/hp/hr)
  • Oil consumption: 0.0067 kg/kW/hr (0.011 lb/hp/hr)
  • Power-to-weight ratio: 1.494 kW/kg (0.909• hp/lb)
  • B.M.E.P.: 1,470 kPa (213 psi)
  • 14R-05 propeller rotates in opposite direction

See also

Related lists


  1. ^ Wilkinson, Paul H. (1946). Aircraft engines of the World 1946 (4th ed.). London: Sir Isaac Pitman & Sons Ltd.
  2. ^ Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (3rd ed.). London: Sir Isaac Pitman & Sons Ltd.
This page was last edited on 23 December 2020, at 19:10
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