Vertipedia - Mil Mi-24

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 devices: 1 Single main rotor

Dedicated control device: 1 Tail rotor

Crew required: 2-3 in Tandem arrangement

Landing gear: Wheels (all retractable)

Key Characteristics

Data on key physical features

Aircraft Details

Data on aircraft configuration, weights, flight performance and equipment

Layout and Dimensions

Weights and Performance

Engine Details

Primary Lift Device

Primary Control Device

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

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

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:

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:

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:

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):

References

References and sources used

Mil Moscow Helicopter Plant 50 Years

Lyubimaya Kniga
1998 (page 198)
Book

Russia's Helicopter World

Vertolet
2000 (page 29)
Book

Russian Helicopters, Ka-27

Russian Нelicopters, JSC
5 July 2017 (page 218)
Website

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Number of engines:	2 Turbines
Max Level Flight Speed:	320 km/h	173 kts
Max Range:	595 km	321 nm
Max Endurance:

Main Rotor Diameter:	17.30 m	56.76 ft
Max Gross Weight (ground):	11,500 kg	25,353 lb