Hirth F-30

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Hirth F-30
Type Four-cylinder two-stroke aircraft engine
National origin Germany
Manufacturer Hirth
Unit cost US$8049 (F-30 model - base price 2009)

The Hirth F-30 is a horizontally opposed four-cylinder, two-stroke, carburetted aircraft engine, with optional fuel injection, designed for use on ultralight aircraft and homebuilts.[1][2][3][4]

Development

The F-30 is equipped with dual capacitor discharge ignition and is free air-cooled, with optional fan cooling. The cylinder walls are electrochemically coated with Nikasil. Standard starting is electric start and recoil start is not an option. The reduction drive system available is the G-40 gearbox with optional reduction ratios of 2.03:1, 2.25:1, 2.64:1, 2.96:1 and 3.33:1. A centrifugal clutch is also available as optional equipment.[1][2][3]

The engine runs on a 50:1 pre-mix of unleaded 93 octane auto fuel and oil.[1][2][3]

Variants

F-30
Four-cylinder horizontally opposed, two-stroke, aircraft engine with a dual 38 mm diaphragm carburetors. Produces 85 hp (63 kW) at 5500 rpm if free-air-cooled or 80 hp (60 kW) at 5500 rpm if fan cooled. It has a factory rated TBO of 1200 hours. In production.[3]
F-30E
Four-cylinder horizontally opposed, two-stroke, aircraft engine with fuel injection. Produces 90 hp (67 kW) at 5500 rpm if free-air-cooled or 85 hp (63 kW) at 5500 rpm if fan cooled. It has a factory rated TBO of 1200 hours. In production.[3]
F-30S
Four-cylinder horizontally opposed, two-stroke, aircraft engine with dual integral pumper carburetors. Produces 100 hp (75 kW) at 6200 rpm if free-air-cooled or 95 hp (71 kW) at 6200 rpm if fan cooled. It has a factory rated TBO of 1000 hours. In production.[2]
F-30ES
Four-cylinder horizontally opposed, two-stroke, aircraft engine with fuel injection. Produces 110 hp (82 kW) at 6200 rpm if free-air-cooled or 105 hp (78 kW) at 6200 rpm if fan cooled. It has a factory rated TBO of 1000 hours. In production.[2]

Applications

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3

Specifications (F-30ES)

Data from Recreational Power Engineering[2]

General characteristics

  • Type: Four-cylinder, two-stroke, horizontally opposed, aircraft engine
  • Bore: 72 mm (2.8 in)
  • Stroke: 64 mm (2.5 in)
  • Displacement: 1042 cc (63.6 cu in)
  • Length: 380 mm (15.0 in)
  • Width: 660 mm (26.0 in)
  • Height: 355 mm (14.0 in)
  • Dry weight: 105 lb (47.6 kg), including starter and exhaust system, 129 lb (58.5 kg) with gearbox, exhaust system and electric start. Fan cooling adds 8.5 lb (3.9 kg)

Components

  • Fuel system: Fuel injection
  • Fuel type: unleaded 93 octane auto fuel
  • Oil system: 50:1 fuel/oil premix or oil injection
  • Cooling system: free air or fan
  • Reduction gear: G-40 gearbox with reduction ratios of 2.03:1, 2.25:1, 2.64:1, 2.96:1 and 3.33:1 available. Optional centrifugal clutch.

Performance

  • Power output: 110 hp (82 kW) at 6200 rpm with free-air cooling, 105 hp (78 kW) at 6200 rpm with fan cooling
  • Compression ratio: 9.5:1

See also

References

  1. ↑ 1.0 1.1 1.2 Cliche, Andre: Ultralight Aircraft Shopper's Guide 8th Edition, pages G-4 Cybair Limited Publishing, 2001. ISBN 0-9680628-1-4
  2. ↑ 2.0 2.1 2.2 2.3 2.4 2.5 Lua error in package.lua at line 80: module 'strict' not found.
  3. ↑ 3.0 3.1 3.2 3.3 3.4 Lua error in package.lua at line 80: module 'strict' not found.
  4. ↑ Purdy, Don: AeroCrafter - Homebuilt Aircraft Sourcebook, page 72. BAI Communications. ISBN 0-9636409-4-1
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