Franklin O-175
(Redirected from Franklin 4AC-176)
| O-175/4AC-176 | |
|---|---|
| Type | Piston aircraft engine |
| National origin | United States |
| Manufacturer | Franklin Engine Company |
| First run | 1940 |
The 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 175 cu in (2.9 L). The power output was nominally 80 hp (60 kW). 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 60 hp (45 kW).
Variants
[edit]O-170
[edit]- 4AC-171
- 60 hp (45 kW)
O-175
[edit]- 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
[edit]- 4AC-176-F3 (O-180-1)
Applications
[edit]- 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)
[edit]Data from Wilkinson[1]
General characteristics
- Type: 4-cylinder air-cooled horizontally opposed aircraft piston engine
- Bore: 4 in (102 mm)
- Stroke: 3.5 in (89 mm)
- Displacement: 176 cu in (2.88 L)
- Length: 28.6 in (726 mm)
- Width: 30.2 in (767 mm)
- Height: 20 in (508 mm)
- Dry weight: 182 lb (82.6 kg)
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 40 psi (3 bar), wet sump
- Cooling system: Air-cooled
Performance
- Power output: 65 hp (48.5 kW) 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
[edit]Related lists
References
[edit]- Notes
- ^ Wilkinson, Paul H. (1945). Aircraft Engines of the world 1945. New York: Paul H. Wilkinson. pp. 88–89.
- Bibliography
- Gunston, Bill. (1986) World Encyclopedia of Aero Engines. Patrick Stephens: Wellingborough. p. 57