|Preserved OX-5 engine|
|Type||V-8 piston engine|
|National origin||United States|
|Manufacturer||Curtiss Aeroplane and Motor Company|
The Curtiss OX-5 was an early V-8 American liquid-cooled aircraft engine built by Curtiss. It was the first American-designed aircraft engine to enter mass production, although it was considered obsolete when it did so in 1917. It nevertheless found widespread use on a number of aircraft, perhaps the most famous being the JN-4 "Jenny". Some 12,600 units were built through early 1919. The wide availability of the engine in the surplus market made it common until the 1930s, although it was considered unreliable for most of its service life. Today, the engine can be found powering many Edwardian automobile racing specials on the historic racing scene.
Design and development
The OX-5 was the last in a series of Glenn Curtiss designed V engines, which started as a series of air-cooled V-twins for motorcycles in 1902. A modified version of one of these early designs was sold as an aircraft engine in 1906, and from then on the company's primary market was aircraft. The basic design had slowly expanded by adding additional cylinders until they reached the V-8 in 1906. They also started enlarging the cylinders as well, but this led to cooling problems that required the introduction of water cooling in 1908. These early engines used a flathead valve arrangement, which eventually gave way to a cross-flow cylinder with overhead valves in 1909, leading to improved volumetric efficiency. The US Navy ordered a version of this basic design in 1912 for its A-1 amphibious aircraft, which Curtiss supplied as the OX. These improvements and others were worked into what became the OX-5, which was first built in 1910. By this point engine design was a team effort; the team included Charles Manley, whose earlier Manley-Balzer engine had held the power-to-weight ratio record for 16 years.
Like most engines of the era, the OX-5's high-temperature areas were built mostly of cast iron, using individual cylinders bolted to a single aluminum crankcase, wrapped in a cooling jacket made of a nickel-copper alloy. Later versions used a brazed-on steel jacket instead. Cylinder heads were also attached to the crankcase, using X-shaped tie-downs on the top of the head attached to the block via four long bolts. Fuel was carbureted near the rear of the engine, then piped to the cylinders via two T-shaped pipes, the cylinders being arranged so the intake ports of any two in a bank were near each other. The cylinders had one intake and one exhaust valve, each operated by a pushrod from a camshaft running between the banks. This arrangement caused the outer exhaust valves to have a rather long rocker arm. The pushrods were arranged one inside the other, the exhaust valve rod being on the inside and the intake valve rod a tube around it. The aluminum camshaft bearings were a split type bolted together and held in place by lock screws. The pistons were cast aluminum.
The OX-5 was not considered particularly advanced, nor powerful, for its era. By this point rotary engines such as the Oberursel or Gnome-Rhone were producing about 100 hp (75 kW), and newer inlines were becoming available with 160 hp (120 kW) or more. Nevertheless, the OX-5 had fairly good fuel economy as a result of its slow RPM, which made it useful for civilian aircraft. The OX-5 was used on the Laird Swallow, Pitcairn PA-4 Fleetwing II, Travel Air 2000, Waco 9 and 10, the American Eagle, the Buhl-Verville CW-3 Airster, and some models of the Jenny. The primary reason for its popularity was its low cost after the war, with almost-new examples selling as low as $20. It was often used in boats as well as in aircraft.
The engine was considered unreliable, but unreliable is a relative term: aviation engine technology had not fully matured at the end of World War I. Certainly the JN4 with the OX-5 was underpowered, but the OX-5 proved a much better engine than the Hall Scott A7A that was the Achilles heel of the Standard J-1, the substitute primary trainer. In particular the valve gear was fragile, and it had no provisions for lubrication other than grease and oil applied by hand, leading to an overhaul interval as short as fifty hours. Additionally the engine featured a single spark plug in each cylinder, and a single ignition system, in an era when ignition equipment was less reliable, with dual ignition being fitted to more advanced aviation powerplants like the French V-form Hispano-Suiza 8 and the inline-six cylinder series of Mercedes D.I through D.III German engines. Built by several contractors in large numbers, the OX-5 suffered from uneven quality control. However, while the overwhelming majority of training accidents in the U.S. were in JN-4s, this was because JN-4s were flown by the vast majority of trainee pilots, and the accident rate in the US for primary training was four times less than the advanced training rate in France (virtually all US airmen getting advanced training in France), approximately 2800 flying hours in the US primarily in OX-5 powered JN-4s per fatality to 761 hours per fatality in France in other types. Very few fatal accidents were caused by engine failure, although the lack of power may have been the cause of the many tailspins that took about forty five percent of training lives. Anyone seeing a JN-4 today struggling into the air with an OX-5 can see very quickly that the JN-4 had to be flown in a narrow envelope. Also, the replacement of the A7A in Standard J-1s was contemplated, but the cost of $2,000 per aircraft compared with the need (by the time the J-1s were grounded in June 1918 JN-4s were in sufficient supply) led to the rejection of this idea. The successful civilian post-war use of the OX-5 (even in civilian purchased and converted J-1s) was due to its relative reliability in the more aerodynamically advanced designs of the 1920s, its simplicity of operation, and its low cost. By comparison the Hall Scott A7A created such a bad impression during the war that very few, if any, were used by civilian operators.
The OX-5 itself would be replaced by the well-proven Wright Aeronautical-built version of the 150 hp Hispano-Suiza HS-8a V8 engine in the nearly 930 examples of the later production Curtiss JN-4H Jenny biplanes.
- Type: 8-cylinder water-cooled 90° Vee piston engine
- Bore: 4.0 in (102 mm)
- Stroke: 5.0 in (127 mm)
- Displacement: 503 in³ (8.2 l)
- Length: 56.75 in (1441.45 mm)
- Width: 29.75 in (755.65 mm)
- Height: 36.75 in (933.45 mm)
- Dry weight: 390 lb (177 kg)
- Valvetrain: One intake and one exhaust valve per cylinder, pushrod-actuated
- Fuel system: Duplex Zenith Carburetor
- Oil system: Gear-pump 40 to 60 psi 3-gallon sump
- Cooling system: Water-cooled
- Power output:
- 90 hp (67 kW) at 1,400 rpm
- 105 hp (78 kW) at 1,800 rpm for brief periods
- Specific power: 0.21 hp/in³ (9.5 kW/l)
- Compression ratio: 4.9:1
- Fuel consumption: 8.0 US gal/h (30.8 l/h) at 75% power
- Specific fuel consumption: 0.53 lb/(hp·h) (0.32 kg/(kW·h)) at 75% power
- Oil consumption: 0.5 US gal/h (1.9 l/h) at 75% power
- Power-to-weight ratio: 0.27 hp/lb (440 W/kg)
- Smith, 1981, page 46
- A reproduction of the A-1 is on display at the San Diego Air & Space Museum
- Smith, 1981, page 12
- Fisher, 2009, page 7
- Gunston, 1995, page 47
- Angle, 1940, pages 244-246
- Smith, 1981, page 47
- Angle, Glenn D., AEROSPHERE 1939. New York: Aircraft Publications, 1940.
- Gunston, Bill, World Encyclopedia of Aero Engines. Somerset: Haynes Publishing, 1995. ISBN 1-85260-509-X
- Fisher, Scott M., The Curtiss OX-5, Aircraft Maintenance Technology. Cygnus Business Media, July 2009.
- Smith, Herschel, Aircraft Piston Engines. McGraw-Hill Book Company, 1981. ISBN 0-07-058472-9
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