Continental O-280

O-280
Type	Piston aircraft engine
National origin	USA
Manufacturer	Continental Motors

The Continental C115, C125 and C140 aircraft engines were made by Continental Motors in the 1940s, all sharing the US military designation O-280. Of flat-6 configuration, the engines produced 115 hp (86 kW) 125 hp (93 kW) or 140 hp (104 kW) respectively.

The C115 was in production from 1945 to 1951, the C125 was in production from 1945 to 1952, and the C140 from 1945 to 1946.

The C125 has the same crankcase as the Continental C145, although the engines differ in stoke, compression ratio and carburetor jetting. The C125 features a cast iron camshaft and hydraulic tappets.^[1]

Applications

C125

Specifications (C125)

Reference: Engines for Homebuilt Aircraft & Ultralights^[1]

General characteristics

Type: 6-cylinder air-cooled horizontally opposed aircraft piston engine
Bore: 4 ¹⁄₁₆ in (4.0625 in resp. 103.12 mm)
Stroke: 3 ⁵⁄₈ in (3.625 in resp. 92.075 mm)
Displacement: 282 in³ (4.6 L)
Length: 39.75 in (101.0 cm)
Width: 31.5 in (80.0 cm)
Height: 23.25 in (59.0 cm)
Dry weight: 286 lb (130 kg)

Components

Cooling system: Air-cooled

Performance

Power output: 125 hp (93 kW) at 2,550 rpm
Specific power: 0.44 hp/in³ (20.2 kW/l)
Compression ratio: 6.3:1
Power-to-weight ratio: 0.43 hp/lb (0.72 kW/kg)

References

1 2 Christy, Joe: Engines for Homebuilt Aircraft & Ultralights, pages 60-62. TAB Books, 1983. ISBN 0-8306-2347-7

Gunston, Bill. (1986) World Encyclopedia of Aero Engines. Patrick Stephens: Wellingborough.
Erickson, Jack. Horizontally-Opposed Piston Aero Engines

Continental Motors aircraft engines

Opposed piston engines
(Gasoline)

By company horsepower designation	A40 A50 A65 A75 A80 C75 C85 C90 C115 C125 C140 C145 E165 E185 E225 Tiara series

By displacement	O-170 O-190 O-200 O-205 O-240 O-280 O-300 IO-346 IO-360 IO-368 O-470 O-520 O-526 IO-550

Aircraft Diesel engines

Radial engines

R-670
R-975

Inverted-V engines

XI-1430

Turboprops

TP-500

United States military piston aircraft engine designation system

H (four-bank H-configuration inline)	H-1640 XH-2240 H-2470 XH-2600 XH-3130 XH-3730 H-4070

I (inverted-V inline)	IV-1430 IV-2040 IV-2220

L (single-bank inline)	L-330 L-365 L-375 L-390 L-410 L-440 L-510 L-825

O (opposed)	O-15 O-40 O-45 O-90 O-100 O-145 O-150 O-170 O-175 O-180 O-190 O-200 (C) O-200 (F) O-205 O-235 O-290 O-300 O-335 O-360 (C) O-360 (L) O-405 O-425 O-435 O-470 O-480 O-520 O-540 (F) O-540 (L) O-550 O-580 O-805 O-1230

R (radial)	R-250 R-265 R-270 R-370 (LB) R-370 (K) R-420 R-440 R-500 R-540 (W) R-540 (K) R-545 R-550 R-600 R-670 R-680 R-720 R-755 R-760 R-790 R-830 R-915 R-975 DR-980 R-985 R-1044 R-1300 R-1340 R-1454 R-1510 R-1535 R-1640 R-1670 R-1690 R-1750 R-1820 R-1830 R-1860 R-2000 R-2060 R-2160 R-2180 R-2600 R-2800 R-3350 R-4090 R-4360 XR-7755

V (upright-V inline)	V-720 V-770 V-1150 V-1237 V-1400 V-1410 V-1440 V-1460 V-1510 V-1560 V-1570 V-1650 (L) V-1650 (P) V-1710 V-1950 V-3420

W (three-bank W-configuration inline)	W-2779

See also: X-1800 US military gas turbine aeroengines Piston engine configurations

This article is issued from Wikipedia - version of the 11/30/2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.