Piaggio P.XI
| P.XI | |
|---|---|
| |
| Preserved Piaggio P.XI | |
| Type | Radial engine |
| Manufacturer | Piaggio |
| Developed from | Gnome-Rhône Mistral Major |
The Piaggio P.XI was an Italian 14-cylinder radial aircraft engine. The P.XI was a licensed derivative of the French Gnome-Rhône Mistral Major 14K produced in Italy.[1]
Further development led to the P.XIX. This featured an increased compression ratio from 6:1 to 7:1 and an rpm increase from 2,400 to 2,600.
Variants[edit]
- P.XI
- P.XIbis
- P.XI R.C.15
- (geared, rated altitude 1,500 m (4,900 ft))
- P.XI R.C.30
- (geared, rated altitude 3,000 m (9,800 ft))
- P.XI R.C.40D
- [2]
- P.XI R.C.40S
- 740 kW (1,000 PS) (geared, rated altitude 4,000 m (13,000 ft)), opposite rotation to 40D.
- P.XI R.C.40bis
- (geared, rated altitude 4,000 m (13,000 ft))
- P.XI R.2C.40
- 740 kW (1,000 PS), (geared, rated altitude 4,000 m (13,000 ft)), two-speed supercharger.
- P.XI C.40
- (direct drive, rated altitude 4,000 m (13,000 ft))
- P.XI R.C.44
- (geared, rated altitude 4,400 m (14,400 ft))
- P.XI R.C.50
- (geared, rated altitude 5,000 m (16,000 ft))
- P.XI R.C.60
- (geared, rated altitude 6,000 m (20,000 ft))
- P.XI R.C.72
- (geared, rated altitude 7,200 m (23,600 ft))
- P.XI R.C.l00
- P.XI R.C.100/2v
- (geared, rated altitude 10,000 m (33,000 ft))
Applications[edit]
- Breda Ba.65
- Breda Ba.88
- CANT Z.516
- CANT Z.1007
- Caproni Ca.135
- Caproni Ca.161
- Reggiane Re 2000
- Saab 17C
- Savoia-Marchetti SM.79B
- Savoia-Marchetti SM.84
Specifications (P.XI R.C.40)[edit]
Data from Italian Civil & Military Aircraft 1930-1945 and Aircraft Engines of the World 1945.[3][4]
General characteristics
- Type: 14-cylinder radial engine
- Bore: 146 mm (5.75 in)
- Stroke: 165 mm (6.50 in)
- Displacement: 38.6 L (2,356 cu in)
- Length: 1,700 mm (66.9 in)
- Diameter: 1,328 mm (52.3 in)
- Dry weight: 650 kg (1,433 lb)
- Frontal Area: 1.39 m2 (15.0 sq ft)
Components
- Valvetrain: 2 x overhead valves per cylinder operated by rockers and pushrods
- Supercharger: Centrifugal compressor, geared to 7.9:1
- Fuel system: 1 x Piaggio T2-100 dual downdraught carburettor with automatic boost and mixture control
- Fuel type: 87 octane
- Oil system: Pressure fed at 483 kPa (70 psi), dry sump
- Cooling system: Air
- Reduction gear: Epicyclic reduction gear ratio 0.62:1
- Starter: Garelli compressed air starter
- Ignition: 2 x Marelli MF14 magnetos, 2 x spark plugs per cylinder fed by a shielded ignition harness.
Performance
- Power output:
- Take-off: 1,000 PS (735 kW) at 2,200rpm
- Military: 1,000 PS (735 kW) at 2,200rpm at 4,000 m (13,000 ft)
- Cruising: 1,000 PS (735 kW) at 1,800rpm at 4,000 m (13,000 ft)
- Specific power: 19.1 kW/L (0.49 hp/cu in)
- Compression ratio: 6.0:1
- Specific fuel consumption: 0.292 kg/kW/hr (0.48 lb/hp/hr)
- Oil consumption: 0.0134 kg/k/w/hr (0.022 lb/hp/hr)
- Power-to-weight ratio: 1.15 kW/kg (0.699 hp/lb)
See also[edit]
Related development
Related lists
References[edit]
Wikimedia Commons has media related to Piaggio P.XI.
Notes[edit]
- ^ Gunston 1989, p.110.
- ^ Grey, C.G.; Bridgman, Leonard (1938). Jane's All the World's Aircraft 1938. London: Sampson Low, Marston & company, ltd. :740 kW (1,000 PS) (geared, rated altitude 4,000 m (13,000 ft))
- ^ Thompson, Jonathan (1963). Italian Civil & Military Aircraft 1930-1945. New York: Aero Publishers Inc. ISBN 0-8168-6500-0. LCCN 63-17621.
- ^ Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (2nd ed.). London: Paul H. Wilkinson. pp. 306–307.
Bibliography[edit]
- Thompson, Jonathan (1963). Italian Civil & Military Aircraft 1930-1945. New York: Aero Publishers Inc. ISBN 0-8168-6500-0. LCCN 63-17621.
- Wilkinson, Paul H. (1945). Aircraft engines of the World 1945 (2nd ed.). London: Paul H. Wilkinson. pp. 306–307.
- Grey, C. G.; Bridgman, Leonard (1938). Jane's All the World's Aircraft 1938. London: Sampson Low, Marston & company, ltd.
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9