Lycoming O-290
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| 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.
Contents
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
Provision for cylinder and oil cooling; for Firestone XR-9 helicopter[citation needed]
- O-290-7
Provision for cylinder and oil cooling; for Firestone XR-9 helicopter[citation needed]
- O-290-9
- No.10 spline used on prop shaft[citation needed]
- O-290-11
- Identical to the O-290-D[1]
Applications
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2
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
See also
- Related lists
References
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- ↑ 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.
