Isotta Fraschini Delta
The Delta was a 12-cylinder inverted-V aircraft engine built by Isotta Fraschini prior to and during World War II.[1]
Design and development
The Delta is a fairly rare example of a large air-cooled inline engine, which normally have cooling problems with the rearmost cylinders. It produced about 750 hp in common versions, although others were rated up to 900 hp. The Delta was not widely used, although it could be found on a number of production aircraft and some advanced prototypes.
The engine included a number of otherwise advanced features. For instance, the valves were powered by dual overhead cams driven by power shafts at the rear of the engine. Exhaust ports were arranged to exit toward the middle of the engine, one cylinder bank being the mirror of the other, allowing the piping to be ganged below the engine nacelle.
Variants
- Delta R.C.20/55 ID-IS
- Delta R.C.21/60
- Delta R.C.35
- Delta R.C.35 I
- Delta R.C.35 IS
- Delta R.C.40 IS
- Delta R.C.40 ID-IS
- Delta R.C.48
- Delta III R.C.40
- Delta IV R.C.17/50
Applications
- Ambrosini SAI.107
- Ambrosini SAI.207 prototype
- Ambrosini SAI.403 prototype
- CANT Z.515
- Caproni Ca.313
- Caproni Ca.314
- Caproni Ca.331
- Caudron C.714 (C.760) prototype
- Henschel Hs 129 prototype
- Reggiane Re.2001 prototype
- Savoia-Marchetti SM.86
Specifications (Delta RC35-IDS)
Data from Aircraft engines of the World.[2]
General characteristics
- Type: 12-cylinder air-cooled 60 degree inverted vee
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- Dry weight: 510 kg (1,124 lb)
Components
- Valvetrain: Two poppet valves per cylinder, sodium cooled exhaust valves, double overhead camshafts
- Supercharger: Single-stage, single-speed centrifugal type supercharger, gear ratio 9.8:1
- Fuel system: Four Isotta Fraschini downdraft carburetors
- Fuel type: 80/87 octane petrol (aviation gasoline)
- Oil system: Dry sump, double scavenge pump, single pressure pump
- Cooling system: Air-cooled
- Reduction gear: Ratio 0.64:1
Performance
- Power output:
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- Specific power: 21.5 kW/L (0.47 hp/in³)
- Compression ratio: 6.4:1
- Specific fuel consumption: 270 grams/hp*hour maximum, 250 grams/hp*hour cruise (70%)
- Power-to-weight ratio: 1.1 kW/kg (0.68 hp/lb)
See also
Comparable engines
Related lists
References
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Bibliography
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- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. Template:ISBN
- Jane's Fighting Aircraft of World War II. London. Studio Editions Ltd, 1989. Template:ISBN
- Wilkinson, Paul H. Aircraft engines of the World 1945. New York, Paul H. Wilkinson, 1945.