Franklin O-175
Template:Short description Template:Use dmy dates Template:Use American English
Template:Infobox Aircraft EngineThe Franklin O-175 (company designation 4AC-176) was an American air-cooled aircraft engine of the 1940s. The engine was of horizontally-opposed four-cylinder and displaced Script error: No such module "convert".. The power output was nominally Script error: No such module "convert".. A later variant was designated O-180, despite sharing the same displacement.
A related four-cylinder engine of slightly smaller capacity was known as the O-170 or 4AC-171. It produced Script error: No such module "convert"..
Variants
O-170
- 4AC-171
- Script error: No such module "convert".
O-175
- 4AC-176
-
- 4AC-176-B - 65 hp (48 kW) at 2,200 rpm
- 4AC-176-BA/(O-175-1) - 65 hp (48 kW) at 2,300 rpm
- 4AC-176-C - 75 hp (56 kW) at 2,500 rpm
- 4AC-176-D - 80 hp (60 kW) at 2,650 rpm
- 4AC-176-F - 80 hp (60 kW) at 2,500 rpm
- 4ACG-176
O-180
- 4AC-176-F3 (O-180-1)
Applications
- Aeronca L-3D
- Bowyer BW-1 flying wing
- CAP-4 Paulistinha
- Harris Little Jewel
- Interstate Cadet
- IPT-7 Junior
- Jensen Sport (O-170)
- Johnson-Funke monoplane
- Langley Twin
- Piper J-3 Cub
- Piper J-4
- Piper L-4
- Porterfield Collegiate
- Taylorcraft BF-60 (O-170)
- Taylorcraft BF-65
Specifications (4AC-176-BA2, O-175-1)
Data from Wilkinson[1]
General characteristics
- Type: 4-cylinder air-cooled horizontally opposed aircraft piston engine
- Bore: Script error: No such module "convert".
- Stroke: Script error: No such module "convert".
- Displacement: Script error: No such module "convert".
- Length: Script error: No such module "convert".
- Width: Script error: No such module "convert".
- Height: Script error: No such module "convert".
- Dry weight: Script error: No such module "convert".
Components
- Valvetrain: OHV, 1x inlet valve, 1x exhaust valve operated by pushrods
- Fuel system: 1x Marvel-Schebler MA-3P updraught carburetor
- Fuel type: 73 octane gasoline
- Oil system: Pressure system at Script error: No such module "convert"., wet sump
- Cooling system: Air-cooled
Performance
- Power output: Script error: No such module "convert". at 2,300 rpm for take-off
- Specific power: 0.37 hp/(cu in) (16.837 kW/L)
- Compression ratio: 6:1
- Specific fuel consumption: 0.49 lb/(hp h) (0.298 kg/(kW h), 220 US gal/(hp h)) cruising
- Oil consumption: 0.003 lb/(hp h) (0.0018 kg/(kW h), 1.4 US gal/(hp h)) cruising
- Power-to-weight ratio: 0.357 hp/lb (0.587 kW/kg)
See also
Related lists
References
- Notes
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- ↑ Script error: No such module "citation/CS1".
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- Bibliography
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- Gunston, Bill. (1986) World Encyclopedia of Aero Engines. Patrick Stephens: Wellingborough. p. 57
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