IAR K14
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| IAR K14 | |
|---|---|
| 300px | |
| Preserved Piaggio P.XI | |
| Type | Radial engine |
| National origin | Romania |
| Manufacturer | Industria Aeronautică Română |
| First run | 1937 |
| Major applications | IAR 80, IAR 37, IAR 39 |
| Number built | 1000 |
| Developed from | Gnome-Rhône Mistral Major |
The IAR K14 was a Romanian 14-cylinder radial aircraft engine. The IAR K14 was a licensed derivative of the French Gnome-Rhône Mistral Major 14K produced in Romania.[1]
Contents
Variants
- IAR K14-II C32 693 kW (930 hp) engine. 44 for IAR P.24E
- IAR K14-II C32 - 649 kW (870 hp) engine. 50 built for IAR 37, 1 built for IAR 80 prototype
- IAR K.14-III C36 - 690 kW (930 hp) engine. 20 built for IAR 80, 95 built for IAR 37
- IAR K.14-IV C32 - 716 kW (960 hp) engine. 30 built for IAR 80, 160 built for IAR 39, 2 built for IAR 47 prototypes
- IAR K.14-IV C32 1000A - 764 kW (1025 hp) engine. 430 built for IAR 80A,IAR 80B,IAR 80C, IAR 81A,IAR 81B,IAR 81C
Applications
- Industria Aeronautică Română IAR P.24E
- Industria Aeronautică Română IAR 37
- Industria Aeronautică Română IAR 39
- Industria Aeronautică Română IAR 47
- Industria Aeronautică Română IAR 80
- Industria Aeronautică Română IAR 81
- Savoia-Marchetti SM 79B Romanian type
Specifications
General characteristics
- Type: Fourteen-cylinder two-row air-cooled radial engine
- Bore: 146 mm (5.748 in)
- Stroke: 165 mm (6.496 in)
- Displacement: 38.673 l (2,360 in³)
- Diameter: 1,296 mm (51.02 in)
- Dry weight: 540 kg (1,190 lb)
Components
- Valvetrain: Overhead valves
- Supercharger: Single-speed centrifugal type supercharger
- Fuel system: Stromberg carburetor
- Fuel type: 87 octane rating gasoline
- Cooling system: Air-cooled
- Reduction gear: 2:3
Performance
- Power output:
- 743 kW (996 hp) at 2,390 rpm for takeoff
- 821 kW (1,100 hp) at 2,390 rpm at 2,600 m (8,530 ft)
- Specific power: 21.23 kW/l (0.47 hp/in³)
- Compression ratio: 5.5:1
- Specific fuel consumption: 328 g/(kW•h) (0.54 lb/(hp•h))
- Oil consumption: 20 g/(kW•h) (0.53 oz/(hp•h))
- Power-to-weight ratio: 1.52 kW/kg (0.92 hp/lb)
See also
- Related development
- Comparable engines
- Related lists
References
Notes
- ↑ Gunston 1989,
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
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