The Ka-22 Vintokryl ('Screw Wing') was a large twin-turboshaft powered convertiplane that debuted at the Soviet National Aviation Day display on 9 July 1961 in Tushino. At each end of the high, straight wing, was a 6,500 shp Soloviev D-25VK engine which powered a four-bladed rotor for vertical flight and a four-bladed propeller for cruise. Each engine was progressively clutched between the two systems to transition between the two modes of flight. The engine was a nine-stage single spool turboshaft modified from the 5,500 shp D-25V engine used on the Mil Mi-6, Mi-10, and V-12 helicopters. The final turbine stage was a free-wheel that drove the gearbox. The fuselage housed a loading ramp that could be used for freight or vehicles, and could carry 36,400 lb of cargo or 80 seats (although this was never done). The tricycle landing gear was fixed and the entire nose area was glazed for good visibility, especially in landing. The high flight deck accommodated two pilots, a radio operator and engineer.

Flight testing began on 20 April 1960. On 7 October 1961, the Vintokryl set a Class E. II speed record of 221.4 mph over a 15/25 km course. On 24 November 1961, it lifted a record payload of 36,343 lb to a height of 6,562 ft (2 km), as well as several other payload to altitude records. The Ka-22 was abandoned after a crash in 1964.

Source: AHS V/STOL Wheel

Overview

Data on design, manufacture and status

Design authority: Kamov Design Bureau

Primary manufacturer: Kamov

Parent type: No type defined

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Compound type: Lift and Thrust

Lift configuration: Tandem (Lateral) (x2)

Dedicated propulsion devices: 2

Crew required: 4

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Layout and Dimensions

Data on aircraft size

Overall Dimensions
Overall Height: 10.70 m 35.1 ft
Overall Length: 27.00 m 88.6 ft
Overall Width:  
Airframe Dimensions
Airframe Length: 27.00 m 88.6 ft
Airframe Width: 23.00 m 75.5 ft
Airframe Height: 10.70 m 35.1 ft
Landing Gear Dimensions
Landing Gear Base:  
Landing Gear Track:  
Cabin Dimensions
Cabin Internal Height: 2.80 m 9.2 ft
Cabin Internal Length: 17.90 m 58.7 ft
Cabin Internal Width: 3.10 m 10.2 ft

Weights and Performance

Data on aircraft weight and flight characteristics

Weights
Max Gross Weight (ground): 42,500 kg 93,696 lb
Max Gross Weight (airborne):  
Max Take-off Weight: 42,500 kg 93,696 lb
Empty Weight:  
Useful Load:  
Empty Weight Fraction:  
Climb Performance
Max Rate of Climb:  
Hover Performance
Hover Ceiling IGE:  
Hover Ceiling OGE:  
Limitations
Max Level Flight Speed: 345 km/h 186 kts
Never Exceed Speed:  
Service Ceiling: 5,500 m 18,045 ft
Range and Endurance
Max Range: 450 km 243 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: Soloviev D-25VK turbine
Manufacturer: Soloviev Design Bureau
Normal Ratings
Max continuous:  
Take-off / rated: 4050 kW 5429 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: 22.50 m 73.82 ft
RPM:  
Direction of Rotation: Counter-rotating
Hub Type:
Main Rotor Blade Characteristics
Blade Construction:
Blade Chord:  
Blade Tip Geometry: Conventional
Blade Twist:  
Number of Blades: 4
Main Rotor Derived Characteristics
Disc Area: 397.61 m² 4280.0 ft²
Disc Loading: 53.44 kg/m² 10.946 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: Unknown
Direction of Rotation: Unknown
RPM:  
Tail Rotor Blade Characteristics
Number of Blades:  
Blade Construction: N/A
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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Related Public Resources

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