Development of the Russian light multipurpose helicopter, the Ka-26 (NATO designation: 'Hoodlum'), began in 1962.  The removable cabin is capable of carrying either six passengers or 2 stretchers and 3 seats; when removed, a cargo platform or sling can be fitted.  Maximum internal and slung loads are 700 kg and 1000 kg, respectively.

Overview

Data on design, manufacture and status

Design authority: Kamov Design Bureau

Primary manufacturer: Kamov

Parent type: Kamov Ka-26

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Coaxial (x2)

Crew required: 1

Crew seating: Single seater

Landing gear: Wheels (non-retractable)

Overall Dimensions

Data on aircraft size

Overall Height: 4.05 m (13.3 ft)

Overall Length: 13.00 m (42.7 ft)

Overall Width: 13.00 m (42.7 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 2

Engine designation: Vedeneyev M-14V26 reciprocating

Engine manufacturer: Vedeneyev

Take-off / rated power: 242 kW (325 hp)

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 3250 kg (7165 lb)

Max Range: 510 km (275 nm)

Max Endurance: 5.2 hrs (5.2 hrs)

Related VFS Resources

Resources related to the Ka-26 , provided by the Vertical Flight Society.
Forum Proceedings
 
Vertiflite articles
Enter a search term in the box above.
Web files from vtol.org
Enter a search term in the box above.
Webpages from vtol.org
Enter a search term in the box above.

Related Public Resources

Resources related to the Ka-26 , provided by public sources across the internet.

Images