A modification of the Mi-1, the Mi-2 was the first Russian light helicopter (NATO Designation: 'Hoplite') powered with two turboshaft engines.  Although initially built and test flown in the USSR all subsequent development and production was carried  out by WSK in Swidnik, Poland. (now PZL-Świdnik). Development began in 1960 and the Mi-2 became widely used in both the armed forces and civil aviation after it began production in 1965.  The aircraft may be fitted with a sling system with a load capacity of 800 kg and a load hoist with a lifting capacity of 260 kg.  The cabin can carry eight passengers in addition to the pilot.

Overview

Data on design, manufacture and status

Design authority: OKB Mil

Latest or last primary manufacturer: WSK-Świdnik
Originally manufactured by OKB Mil

Parent type: Mil Mi-2

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-2

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length:  
Overall Width: 14.50 m 47.6 ft
Airframe Dimensions
Airframe Length: 11.94 m 39.2 ft
Airframe Width: 1.60 m 5.2 ft
Airframe Height: 3.75 m 12.3 ft
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height: 1.20 m 3.9 ft
Cabin Internal Length: 2.27 m 7.4 ft
Cabin Internal Width: 1.45 m 4.8 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Weights
Max Gross Weight (ground): 3,700 kg 8,157 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 3,700 kg 8,157 lb
Empty Weight: 2,350 kg 5,181 lb
Useful Load: 1,350 kg 2,976 lb
Empty Weight Fraction: 0.635
Climb Performance
Max Rate of Climb: 5 m/s 886 fpm
Hover Performance
Hover Ceiling IGE: 1,700 m 5,577 ft
Hover Ceiling OGE: 1,000 m 3,281 ft
Limitations
Max Level Flight Speed: 210 km/h 113 kts
Never Exceed Speed:  
Service Ceiling: 4,000 m 13,123 ft
Range and Endurance
Max Range: 350 km 189 nm
Max Endurance: 4 hrs 4 hrs

Engine Details

Aircraft powerplant (lift and/or propulsion)

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

Powerplant
Number of engines: 2
Designation: Klimov GTD-350 turbine
Manufacturer: JSC Klimov United Engine Corporation
Normal Ratings
Max continuous:  
Take-off / rated: 298 kW 400 hp
Intermediate:  
Maximum:  
OEI Ratings
OEI contingency:  
OEI continuous: 198 kW 265 hp
OEI 30-second:  
OEI intermediate:  

Primary Lift Device

Data on primary lift devices such as main rotors

Main Rotor Characteristics
Diameter: 14.50 m 47.57 ft
RPM:  
Direction of Rotation: Clockwise
Hub Type:
Main Rotor Blade Characteristics
Blade Construction: All-metal
Blade Chord:  
Blade Tip Geometry: Conventional
Blade Twist:  
Number of Blades: 3
Main Rotor Derived Characteristics
Disc Area: 165.13 m² 1777.5 ft²
Disc Loading: 22.41 kg/m² 4.589 lb/ft²
Solidity:  
Main Rotor Blade Derived Characteristics
Blade area per blade:  
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter:  
Configuration: Pusher
Direction of Rotation: Top blade fwd
RPM:  
Tail Rotor Blade Characteristics
Number of Blades: 2
Blade Construction: All-metal
Blade Chord:  
Blade Twist:  
Tail Rotor Derived Characteristics
Disc Area:  
Solidity:  
Tail Rotor Blade Derived Characteristics
Tip Speed:  
Blade Area (per blade):  

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