Nelson H-63
The Nelson H-63, known in the US military designation system as the YO-65, is an American dual ignition, four-cylinder, horizontally opposed, two-stroke aircraft engine that was developed by the Nelson Engine Company for use in helicopters and light aircraft. The engine designation means horizontally opposed 63 cubic inch displacement.[1]
| Nelson H-63 | |
|---|---|
| Type | Two-stroke aircraft engine |
| National origin | United States |
| Manufacturer | Nelson Engine Company |
| Major applications | Hiller YROE |
Design and development
The H-63 was designed in the late 1950s specifically to power the sort of very light single-man helicopters that the US Army was investigating at the time. Application for certification was made on 15 March 1958, and the engine was certified under the CAR 13 standard on 8 February 1960.[1]
Engines were produced for Nelson by the Franklin Engine Company of Syracuse, New York under a production certificate. Originally the type certificate was held by the Nelson Specialty Corporation of San Leandro, California, but it was transferred to Nelson Aircraft of Irwin, Pennsylvania on 15 July 1966. Ownership of the type certificate was transferred to the present owner, Charles R. Rhoades of Naples, Florida, on 14 February 1996.[1]
The four-cylinder engine runs on a 16:1 mixture of 80/87 avgas and SAE 30 outboard motor oil. It is equipped with a single Nelson E-500 carburetor.[1]
Variants
- H-63A
- 42 hp @ 4000 rpm
- H-63C
- Vertically mounted version for use in helicopters, producing 43 hp (32 kW) at 4000 rpm.[1]
- H-63CP
- Horizontally mounted version for use in light aircraft, producing 48 hp (36 kW) at 4400 rpm for take-off.[1]
- YO-65-2
- Military designation for H-63 fitted to the Hiller XROE-1 Rotorcycle
Engines on display
Specifications (H-63C)
Data from FAA Type Certificate Data Sheet,[1] Aircraft engines of the World 1957[3]
General characteristics
- Type: Four-cylinder, two-stroke, dual ignition, vertically mounted helicopter engine
- Bore: 2.6875 in (68 mm)
- Stroke: 2.75 in (70 mm)
- Displacement: 63 cubic inches
- Length: 18 in (460 mm)
- Width: 25 in (640 mm)
- Height: 17.5 in (440 mm)
- Dry weight: Bare engine: 53 lb (24 kg) ; 76 lb (34 kg) including the cooling fan, cooling shroud and clutch
Components
- Valvetrain: 2-stroke valveless
- Fuel system: Nelson E-500 carburetor
- Fuel type: 80/87 avgas
- Oil system: premixed oil in fuel, SAE 30 outboard motor oil mixed at 16:1 fuel to oil
- Cooling system: fan forced air
- Reduction gear: none
Performance
- Power output: 42 hp (31 kW) at 4000 rpm
- Specific power: 0.67 hp/cu in (30 kW/L)
- Compression ratio: 8:1
- Specific fuel consumption: 0.73 lb/(hp⋅h) (440 g/kWh) (maximum)
- Oil consumption: 0.09 lb/hp/h (0.015 kg/kW/ks) (maximum)
- Power-to-weight ratio: 1.26 lb/hp (0.77 kg/kW)
References
- Federal Aviation Administration (February 1996). "Aircraft Type Certificate Data Sheet 4E1" (PDF). Retrieved March 13, 2011.
- Experimental Aircraft Association (2011). "Lobet/Shafor Ganagobie". Archived from the original on July 19, 2011. Retrieved March 13, 2011.
- Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 250.