• Source: 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.


      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.
      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.
      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.


      Variants


      H-63A
      42 hp @ 4000 rpm
      H-63C
      Vertically mounted version for use in helicopters, producing 43 hp (32 kW) at 4000 rpm.
      H-63CP
      Horizontally mounted version for use in light aircraft, producing 48 hp (36 kW) at 4400 rpm for take-off.
      YO-65-2
      Military designation for H-63 fitted to the Hiller XROE-1 Rotorcycle


      Applications


      H-63A
      Goodyear Inflatoplane
      H-63C
      Hiller YROE
      H-63CP
      Lobet/Shafor Ganagobie


      Engines on display


      EAA AirVenture Museum


      Specifications (H-63C)


      Data from FAA Type Certificate Data Sheet, Aircraft engines of the World 1957


      = 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)


      See also


      List of aircraft engines


      References

    Kata Kunci Pencarian: