Development of the Russian Mi-38 medium multipurpose helicopter began in 1981; and there was a presentation at the 1992 Moscow Aeroshow.  Prodcution of the series was facilitated by Kazan Helicopters JSC, as of the year 2000.  Initial versions of the twin-engined aircraft wielded either the BK-2500 or PW-127T/V engines.  Maximum internal and slung loads are 6000 kg and 7000 kg, repectively; passenger capacity is 32 or 16 stretchers.  The helicopter is equipped with GPS and PNKB-38 navigation systems; the main rotor may also be folded.

Data is based on the year 2017 data points of the fourth protoype and 2000 Russia's Helicopter World catalog data points of the Mi-38.

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-38

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-3

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: 21.10 m 69.2 ft
Airframe Dimensions
Airframe Length: 19.95 m 65.5 ft
Airframe Width: 4.30 m 14.1 ft
Airframe Height: 6.15 m 20.2 ft
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height: 1.84 m 6.0 ft
Cabin Internal Length: 7.00 m 23.0 ft
Cabin Internal Width: 1.84 m 6.0 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Cruise Speed: 285 km/h

Weights
Max Gross Weight (ground): 15,600 kg 34,392 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 15,600 kg 34,392 lb
Empty Weight: 8,300 kg 18,298 lb
Useful Load: 7,300 kg 16,094 lb
Empty Weight Fraction: 0.532
Climb Performance
Max Rate of Climb: 9 m/s 1,772 fpm
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE: 3,750 m 12,303 ft
Limitations
Max Level Flight Speed: 290 km/h 157 kts
Never Exceed Speed:  
Service Ceiling: 5,900 m 19,357 ft
Range and Endurance
Max Range:  
Max Endurance:  

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 TV7-117V turbine
Manufacturer: JSC Klimov United Engine Corporation
Normal Ratings
Max continuous:  
Take-off / rated: 2088 kW 2799 hp
Intermediate:  
Maximum:  
OEI Ratings
OEI contingency: 2610 kW 3499 hp
OEI continuous:  
OEI 30-second: 2796 kW 3748 hp
OEI intermediate: 2237 kW 2999 hp

Primary Lift Device

Data on primary lift devices such as main rotors

The main rotor is fold-able for storage and transport.

Main Rotor Characteristics
Diameter: 21.10 m 69.23 ft
RPM:  
Direction of Rotation: Counterclockwise
Hub Type: Elastomeric Bearing
Main Rotor Blade Characteristics
Blade Construction: Composite
Blade Chord:  
Blade Tip Geometry: Swept
Blade Twist:  
Number of Blades: 6
Main Rotor Derived Characteristics
Disc Area: 349.67 m² 3763.9 ft²
Disc Loading: 44.61 kg/m² 9.138 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 hubs are locaed to provide non-90 deg spacing between blades of each hub

Tail Rotor Characteristics
Diameter:  
Configuration: Tractor
Direction of Rotation: Top blade aft
RPM:  
Tail Rotor Blade Characteristics
Number of Blades: 4
Blade Construction: Asymmetrical X-shape
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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