Lycoming O-290

O-290
Type	Piston aircraft engine
Manufacturer	Lycoming Engines
First run	1939
Major applications	Aero Commander 100 Taylorcraft Auster V Piper PA-20 Pacer Seibel S-4
Developed into	Lycoming O-435

The Lycoming O-290 is a dual ignition, four-cylinder, air-cooled, horizontally opposed aircraft engine. It was first run in 1939, and entered production three years later.

A common variant of the type is the O-290-G, a single ignition model which was designed to drive a generator as part of a ground power unit.

Variants

Civil models

O-290: Base model engine certified 27 July 1942. 125 hp (93 kW) at 2450 rpm, 6.25:1 compression ratio, dry weight 244 lb (111 kg)^[1]
O-290-A: Certified 27 July 1942. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 251 lb (114 kg) with SR4L-8 or N-8 magnetos, 245 lb (111 kg) with N-20 or N-21 magnetos.^[1]
O-290-AP: Certified 21 July 1944. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 251 lb (114 kg) with SR4L-8 or N-8 magnetos, 245 lb (111 kg) with N-20 or N-21 magnetos.^[1]
O-290-B: Certified 22 January 1943. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 247 lb (112 kg).^[1]
O-290-C: Certified 22 January 1943. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 238 lb (108 kg).^[1]
O-290-CP: Certified 21 July 1944. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 238 lb (108 kg).^[1]
O-290-D: Certified 13 December 1949. 125 hp (93 kW) at 2600 rpm continuous, 130 hp (97 kW) at 2800 rpm for 5 minutes, 6.5:1 compression ratio, dry weight 230 lb (104 kg).^[1]
O-290-D2: Certified 1 May 1952. 135 hp (101 kW) at 2600 rpm continuous, 140 hp (104 kW) at 2800 rpm for 5 minutes, 7.5:1 compression ratio, dry weight 233 lb (106 kg).^[1]
O-290-D2A: Certified 20 April 1953. 135 hp (101 kW) at 2600 rpm continuous, 140 hp (104 kW) at 2800 rpm for 5 minutes, 7.5:1 compression ratio, dry weight 236 lb (107 kg).^[1]
O-290-D2B: Certified 30 September 1954. 135 hp (101 kW) at 2600 rpm continuous, 140 hp (104 kW) at 2800 rpm for 5 minutes, 7.0:1 compression ratio, dry weight 236 lb (107 kg).^[1]
O-290-D2C: Certified 8 May 1961. 135 hp (101 kW) at 2600 rpm continuous, 140 hp (104 kW) at 2800 rpm for 5 minutes, 7.0:1 compression ratio, dry weight 235 lb (107 kg).^[1]
O-290-G: Non-certified, single ignition model intended for use driving a generator in a ground power unit, 125 hp (93 kW). Has been widely used in homebuilt aircraft, including the prototype Van's Aircraft RV-3.^[2]

Military models

O-290-1: Identical to the O-290-B^[1]
O-290-3: Identical to the O-290-C^[1]
XO-290-5

Provision for cylinder and oil cooling; for Firestone XR-9 helicopter

O-290-7

Provision for cylinder and oil cooling; for Firestone XR-9 helicopter

O-290-9: No.10 spline used on prop shaft
O-290-11: Identical to the O-290-D^[1]

Applications

Specifications (O-290-D2A)

Data from Operator's Manual, Textron Lycoming Aircraft Engines.^[3]

General characteristics

Type: 4-cylinder air-cooled horizontally opposed piston aircraft engine
Bore: 4.875 in (123.8 mm)
Stroke: 3.875 in (98.4 mm)
Displacement: 289 cu in (4.74 L)
Dry weight: 264 lb (119.7 kg)

Components

Valvetrain: Pushrod-actuated valves
Fuel system: Carburetor
Cooling system: Air-cooled

Performance

Power output: 140 hp (104 kW) at 2,800 rpm
Specific power: 0.48 hp/in³ (22.2 kW/L)
Compression ratio: 7.5:1

References

1 2 3 4 5 6 7 8 9 10 11 12 13 14 Federal Aviation Administration (June 1963). "Type Certificate Data Sheet NO. E-229" (PDF). Retrieved 7 September 2010.
↑ EAA AirVenture Museum (2010). "Van Grunsven RV-3 Prototype – Specifications". Retrieved 7 September 2010.
↑ Operator's Manual, Textron Lycoming Aircraft Engines, Series O-235 & O-290 60297-9, 4th Edition January 1988, Pages 2-2 & 2-4, Textron Lycoming.

Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens.

Lycoming aircraft engines

Opposed piston engines	O-145 O-233 IO-233 O-235 O-290 O-320 O-340 O-360 (O-360 variants) IO-390 O-435 O-480 O-540 TIO-541 GSO-580 IO-580 IO-720 O-1230

Radial engines and H engines	R-680 R-7755 H-2470

Turbofans	PLF1 ALF 502/YF102 LF 507

Turboprops/Turboshafts	AGT1500 LTS101/LTP101 T53 T55

Aero-derivative marine gas turbines	TF-40

Joint development	Avco (Lycoming)/Pratt & Whitney: T800-APW (Turboshaft)

See also	AlliedSignal Aerospace/Honeywell Aerospace

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

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