Kaman K-17

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The Kaman K-17 was a two-seat experimental helicopter built by Kaman in the late 1950s. It used a system.^[1]

Specifications[]

Data from Jane's All the World's Aircraft 1958-59^[1]

General characteristics

• Crew: 2
• Capacity: 700 lb (318 kg) payload
• Empty weight: 950 lb (431 kg)^{[citation needed]}
• Max takeoff weight: 2,000 lb (907 kg)^{[citation needed]}
• Fuel capacity: 54 US gal (45 imp gal; 200 l) in a single keel mounted tank
• Powerplant: 1 × Blackburn-Turbomeca Turmo 600 turboshaft, 400 shp (300 kW) maximum rating

350 shp (261.0 kW) maximum continuous rating^[2]

driving a Boeing 502 compressor to supply compressed air to the rotor tip-jets

• Main rotor diameter: 37 ft 0 in (11.28 m)
• Main rotor area: 962.24 sq ft (89.395 m²) driven by compressed air tip-jets

Performance

• Cruise speed: 92 mph (148 km/h, 80 kn)
• Endurance: 2 hours 15 minutes at sea level
• Service ceiling: 5,000 ft (1,500 m) hover ceiling
• Rate of climb: 1,260 ft/min (6.4 m/s)

References[]

External links[]

• "Kaman K-17 helicopter - development history, photos, technical data". www.aviastar.org. Retrieved 4 May 2020.