Flown for the first time in the Spring of 1958, the K-17 is the product of U.S. Army and Kaman cooperation.  The helicopter is a cold tip jet system; the engine sends compressed air to the tip-jet nozzles.  The main rotor is flap controlled and the ducted tail rotor is controlled by hydraulic power, allowing change in direction.

 

 

Source: Alex, Ralph P. "Helicopters from 'A to Z', Part III". American Helicopter Society Newsletter, Vol. 7, 1961. Page 5.

Overview

Data on design, manufacture and status

Design authority: Kaman Aircraft Corporation

Primary manufacturer: Kaman Aircraft Corporation

Parent type: No type defined

Aircraft status: No longer flying

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Fenestron/Shrouded tail rotor

Crew required: 2

Crew seating: Side-by-side

Landing gear: Skids

Overall Dimensions

Data on aircraft size

Overall Height: 2.59 m (8.5 ft)

Overall Length: 11.28 m (37.0 ft)

Overall Width: 11.28 m (37.0 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 2

Engine designation: Turbomeca Turmo 600 turbine

Engine manufacturer: Turbomeca

Take-off / rated power: 298 kW (400 hp)

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 907 kg (2000 lb)

Max Endurance: 2.3 hrs (2.3 hrs)

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