Development of the Mi-24 (NATO Designation: 'Hind'), a Russian transport attack helicopter, began in 1967.  In the design, the cockpit is divided per pilot with separately pressurized cabins.  Either TV3-117 (2200 shp) or TV3-117V (2225 shp) turbine engines may be used for the twin-engine aircraft.  Approved on 19 February, 1969; official testing started in June of 1970.

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-24

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 2-3

Crew seating: Tandem

Landing gear: Wheels (all retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height:  
Overall Length:  
Overall Width: 17.30 m 56.8 ft
Airframe Dimensions
Airframe Length: 17.50 m 57.4 ft
Airframe Width: 6.65 m 21.8 ft
Airframe Height: 3.97 m 13.0 ft
Landing Gear Dimensions
Landing Gear Base: 4.39 m 14.4 ft
Landing Gear Track: 3.03 m 9.9 ft
Cabin Dimensions
Cabin Internal Height: 1.45 m 4.8 ft
Cabin Internal Length: 2.50 m 8.2 ft
Cabin Internal Width: 1.20 m 3.9 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Cruise Speed: 228 km/h

Weights
Max Gross Weight (ground): 11,500 kg 25,353 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 11,500 kg 25,353 lb
Empty Weight: 8,500 kg 18,739 lb
Useful Load: 3,000 kg 6,614 lb
Empty Weight Fraction: 0.739
Climb Performance
Max Rate of Climb: 13 m/s 2,461 fpm
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE: 1,400 m 4,593 ft
Limitations
Max Level Flight Speed: 320 km/h 173 kts
Never Exceed Speed:  
Service Ceiling: 4,600 m 15,092 ft
Range and Endurance
Max Range: 595 km 321 nm
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: Motor Sich TV3-117 turbine
Manufacturer: Motor Sich
Normal Ratings
Max continuous:  
Take-off / rated: 1640 kW 2198 hp
Intermediate:  
Maximum:  
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: 17.30 m 56.76 ft
RPM:  
Direction of Rotation: Clockwise
Hub Type:
Main Rotor Blade Characteristics
Blade Construction: All-metal
Blade Chord: 0.580 m 1.90 ft
Blade Tip Geometry: Conventional
Blade Twist:  
Number of Blades: 5
Main Rotor Derived Characteristics
Disc Area: 235.06 m² 2530.3 ft²
Disc Loading: 48.92 kg/m² 10.020 lb/ft²
Solidity: 0.1067
Main Rotor Blade Derived Characteristics
Blade area per blade: 5.02 m² 54.0 ft²
Tip Speed:  

Primary Control Device

Data on primary control devices such as tail rotors

Tail Rotor Characteristics
Diameter:  
Configuration: Tractor
Direction of Rotation: Top blade aft
RPM:  
Tail Rotor Blade Characteristics
Number of Blades: 3
Blade Construction:  
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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