Kaman K-17
The Kaman K-17 was a two-seat experimental helicopter built by Kaman in the late 1950s. It used a cold-jet rotor system.[1]
| K-17 | |
|---|---|
| Role | Experimental helicopter |
| Manufacturer | Kaman Aircraft |
| First flight | 1958 |
| Status | Retired |
| Number built | 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)
- Max takeoff weight: 2,000 lb (907 kg)
- 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
- Bridgman, Leonard, ed. (1958). Jane's All the World's Aircraft 1958-59. London: Jane's All the World's Aircraft Publishing Co. Ltd. p. 319.
- Bridgman, Leonard, ed. (1958). Jane's All the World's Aircraft 1958-59. London: Jane's All the World's Aircraft Publishing Co. Ltd. p. 437.
External links
- "Kaman K-17 helicopter - development history, photos, technical data". www.aviastar.org. Retrieved 4 May 2020.
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