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Lycoming O-290









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






  • 1 Variants


    • 1.1 Civil models


    • 1.2 Military models




  • 2 Applications


  • 3 Specifications (O-290-D2A)


    • 3.1 General characteristics


    • 3.2 Components


    • 3.3 Performance




  • 4 See also


  • 5 References





Variants[edit]



Civil models[edit]



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[edit]



O-290-1

Identical to the O-290-B[1]

O-290-3

Identical to the O-290-C[1]

O-290-11

Identical to the O-290-D[1]



Applications[edit]




  • Adkisson SJ-1 Head Skinner

  • Aerocar

  • Aero Commander 100

  • Aquaflight Aqua I

  • Aydlett A-1

  • Chrislea Super Ace

  • Falconar F11 Sporty

  • Firestone XR-9

  • Flying K Sky Raider

  • Grumman Kitten

  • Isaacs Fury Mk 1

  • Mustang Aeronautics Midget Mustang

  • Pazmany PL-1

  • Pazmany PL-2

  • Piper PA-12

  • Piper PA-18 Super Cub

  • Piper PA-20 Pacer

  • Piper PA-22 TriPacer

  • Rogers Sportaire

  • Seibel S-4

  • Smyth Sidewinder

  • Stolp Starduster

  • Thorp T-18

  • Toyo T-T.10

  • VanGrunsven RV-1

  • Van Lith VI

  • Van's Aircraft RV-3

  • Warner Revolution II

  • Warner Sportster

  • Williams-Cangie WC-1 Sundancer




Specifications (O-290-D2A)[edit]


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[edit]






Related lists


  • List of aircraft engines


References[edit]





  1. ^ abcdefghijklmn Federal Aviation Administration (June 1963). "Type Certificate Data Sheet NO. E-229" (PDF). Retrieved 7 September 2010..mw-parser-output cite.citation{font-style:inherit}.mw-parser-output q{quotes:"""""""'""'"}.mw-parser-output code.cs1-code{color:inherit;background:inherit;border:inherit;padding:inherit}.mw-parser-output .cs1-lock-free a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/6/65/Lock-green.svg/9px-Lock-green.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .cs1-lock-limited a,.mw-parser-output .cs1-lock-registration a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/d/d6/Lock-gray-alt-2.svg/9px-Lock-gray-alt-2.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .cs1-lock-subscription a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/a/aa/Lock-red-alt-2.svg/9px-Lock-red-alt-2.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .cs1-subscription,.mw-parser-output .cs1-registration{color:#555}.mw-parser-output .cs1-subscription span,.mw-parser-output .cs1-registration span{border-bottom:1px dotted;cursor:help}.mw-parser-output .cs1-hidden-error{display:none;font-size:100%}.mw-parser-output .cs1-visible-error{font-size:100%}.mw-parser-output .cs1-subscription,.mw-parser-output .cs1-registration,.mw-parser-output .cs1-format{font-size:95%}.mw-parser-output .cs1-kern-left,.mw-parser-output .cs1-kern-wl-left{padding-left:0.2em}.mw-parser-output .cs1-kern-right,.mw-parser-output .cs1-kern-wl-right{padding-right:0.2em}


  2. ^ EAA AirVenture Museum (2010). "Van Grunsven RV-3 Prototype – Specifications". Retrieved 7 September 2010.


  3. ^ 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.











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