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Mil Mi-34

By Wikipedia,
the free encyclopedia,

An Mil Mi-34
Role Helicopter
National origin Soviet Union / Russia
First flight 1986
Introduction 1989

The Mil Mi-34 (NATO reporting name "Hermit") is a two/four seat light instructional and competition helicopter. It was first flown in 1986 and entered production in 1989. It is capable of performing aerobatic maneuvers, including rolls and loops.


  • Mi-34 "Flying Jeep" - This aircraft burns 40 kg of fuel per hour. It is filled with modern avionics. It is safe to fly with 3 of 9 cylinders off, and is capable of flying with 5 cylinders off. It can fly in any direction, even upside down. Test-pilots have landed the aircraft on a cement barrier to demonstrate its maneuverability. Entered production in 1994. A few aircraft were purchased by the Moscow police. The list price is $350,000.
  • Mi-34A - Luxury version, intended to be powered by an Allison 250-C20R turboshaft engine. So far, none have been built.
  • Mi-34C - Four-seat production model.
  • Mi-34L - This version is intended to be powred by a 350-hp (261-kW) Texron Lycoming TIO-540J piston engine, so far, none have been built.
  • Mi-34M - Powered by two rotary-piston engines.
  • Mi-34M1 and Mi-34M2 - Unbuilt versions.
  • Mi-34P - Police patrol version for Moscow Major Office.
  • Mi-34V or Mi-34VAZ - This version of the Mi-34 is powered by two VAZ-4265 rotary piston engines. Estimated price about USD400,000 (USD20,000 for each engine). Also known as Mi-234.
  • Mi-34S ('S' for "sertified") - one M-14V26V 325 hp (or 370 hp enforced version) engine. take-off mass 1450 kg, cruise speed 170–190 km/h, range 360 km with 145 kg of load, technical range 700 km, maneuverable overload 3 unit ("G").
  • Mi-34UT - trainer with dual control.
  • Mi-44 - proposed development with TV-O-100 engine and refined aerodynamics. A mockup was built in 1987.

Specifications (Mil-34)

Data from {name of first source}

General characteristics

  • Crew: one, pilot
  • Capacity: Three passengers
  • Length: 11.42 m (37 ft 6 in)
  • Rotor diameter: 10.01 m (32 ft 10 in)
  • Height: 2.75 m (9 ft 0 in)
  • Disc area: 78.5 m² (845 ft²)
  • Empty weight: 800 kg (1,760 lb)
  • Max takeoff weight: 1,350 kg (2,790 lb)
  • Powerplant:Vedeneev M-14V-26 9-cylinder radial engine, 240 kW (320 hp)


See also

Comparable aircraft

External links

Text from Wikipedia is available under the Creative Commons Attribution/Share-Alike License; additional terms may apply.

Published in July 2009.

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