Development of the Russian Mi-6 (NATO Designation: 'Hook') heavy transport helicopter began in 1952; production took off in 1957.  Under extreme circumstances, the cargo cabin can hold up to 150 people; in the ambulance version, 41 stretchers and 2 seats.  Normally, the passenger cabin can accommodate 61 passengers.  Maximum internal and slung payloads are 12,000 kg and 8,000 kg, respectively.


Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-6

Aircraft status: No longer flying


Primary flight and mechanical characteristics

VTOL type: Helicopter

Compound type: Lift

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 5-6

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height: 9.86 m 32.3 ft
Overall Length: 41.74 m 136.9 ft
Overall Width: 35.00 m 114.8 ft
Airframe Dimensions
Airframe Length: 33.18 m 108.9 ft
Airframe Width: 3.20 m 10.5 ft
Airframe Height: 9.16 m 30.1 ft
Landing Gear Dimensions
Landing Gear Base: 8.66 m 28.4 ft
Landing Gear Track: 7.92 m 26.0 ft
Cabin Dimensions
Cabin Internal Height: 2.65 m 8.7 ft
Cabin Internal Length: 12.00 m 39.4 ft
Cabin Internal Width: 2.50 m 8.2 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 41,700 kg 91,933 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 41,700 kg 91,933 lb
Empty Weight: 26,500 kg 58,422 lb
Useful Load: 15,200 kg 33,510 lb
Empty Weight Fraction: 0.635
Climb Performance
Max Rate of Climb: 7 m/s 1,280 fpm
Hover Performance
Hover Ceiling IGE: 2,250 m 7,382 ft
Hover Ceiling OGE:  
Max Level Flight Speed: 250 km/h 135 kts
Never Exceed Speed:  
Service Ceiling: 4,500 m 14,764 ft
Range and Endurance
Max Range: 500 km 270 nm
Max Endurance: 3 hrs 3 hrs

Engine Details

Aircraft powerplant (lift and/or propulsion)

Provided powerplant data is for uninstalled, sea level, static operations.

Number of engines: 2
Designation: Soloviev D-25V turbine
Manufacturer: Soloviev Design Bureau
Normal Ratings
Max continuous:  
Take-off / rated: 4103 kW 5500 hp
OEI Ratings
OEI contingency:  
OEI continuous:  
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Main Rotor Characteristics
Diameter: 31.39 m 103.00 ft
RPM: 120.0 rpm 120.0 rpm
Direction of Rotation: Clockwise
Hub Type: Fully articulated
Main Rotor Blade Characteristics
Blade Construction: Metal blades
Blade Chord: 1.158 m 3.80 ft
Blade Tip Geometry: Conventional
Blade Twist:  
Number of Blades: 5
Main Rotor Derived Characteristics
Disc Area: 774.09 m² 8332.6 ft²
Disc Loading: 53.87 kg/m² 11.033 lb/ft²
Solidity: 0.1174
Main Rotor Blade Derived Characteristics
Blade area per blade: 18.18 m² 195.7 ft²
Tip Speed: 197.26 m/s 647.2 fps

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter: 6.40 m 21.00 ft
Configuration: Pusher
Direction of Rotation: Top blade fwd
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction:  
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area: 32.18 m² 346.4 ft²
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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