Kaman K-16B

K-16B
The K-16B with wing at full tilt
Role Experimental tiltwing
National origin United States
Manufacturer Kaman Aircraft
Primary user United States Navy
Number built 1
Developed from Grumman G-21 Goose

The Kaman K-16B was an experimental vertical-takeoff-and-landing aircraft that was constructed by Kaman Aircraft for the United States Navy in 1959 to evaluate the tiltwing concept. Converted from a Grumman Goose amphibian, the K-16B underwent extensive wind tunnel and tethered testing, but was not flown before the project was terminated in 1962.

Design and development

During the late 1950s, there was extensive interest in the vertical takeoff and landing concept for aircraft, with multiple experimental types ordered to develop the technology for potential service. The United States Navy contracted with Kaman Aircraft of Bloomfield, Connecticut to build a testbed based on the company's 'rotorprop' concept for tiltwing aircraft,[1] using a Grumman JRF-5 Goose amphibian and other existing parts to reduce the cost and time necessary.[2] The fuselage and tail of the Goose were mated to a new tilting wing and engine configuration;[3] the maximum angle of incidence allowed was only 50 degrees; the rotorprop was expected to provide sufficient thrust to allow VTOL operations despite the low angle.[1]

Operational history

Delivered in late 1959, the K-16B underwent extensive wind tunnel testing, along with some tethered hops, to evaluate the tiltwing configuration's aerodynamic characteristics.[4] Flight testing was originally anticipated to begin in the fall of 1960,[2] however these preliminary tests continued into 1962.[5] That year the project was cancelled with the aircraft having not conducted its first free flight.[4]

Surviving aircraft

The prototype K-16B is on display at the New England Air Museum in Windsor Locks, Connecticut.[4]

Specifications

The K-16B at the New England Air Museum

Data from Jane's 1959–1960[2] and the New England Air Museum.[4] All performance data estimated.

General characteristics

  • Crew: 2
  • Length: 38 ft 4 in (11.68 m)
  • Wingspan: 34 ft 0 in (10.36 m)
  • Height: 19 ft 2 in (5.84 m)
  • Empty weight: 6,500 lb (2,948 kg)
  • Gross weight: 8,000 lb (3,629 kg)
  • Powerplant: 2 × General Electric YT58-GE-2A turboshafts, 1,324.9 hp (988.0 kW) each
  • Propellers: 3-bladed Kaman, 14 ft 10 in (4.52 m) diameter

Performance

  • Maximum speed: 200 mph (322 km/h; 174 kn)
  • Range: 250 mi (217 nmi; 402 km)
  • Service ceiling: 16,000 ft (4,900 m)

See also

Related development

Aircraft of comparable role, configuration and era

Related lists

References

Citations
  1. 1 2 Swanborough 1964, p.50.
  2. 1 2 3 Jane's 1959–1960, p.331.
  3. ↑ McGowen 2005, p.180.
  4. 1 2 3 4 "Kaman K-16B". New England Air Museum. Windsor Locks, CT. Retrieved 2017-12-02.
  5. ↑ "Kaman K-16 in 40x80 Foot Wind Tunnel at Ames Research Center". Photo A-29884-2. NASA Ames Research Center. 19 September 1962. Retrieved 2017-12-02.
Bibliography

  • McGowen, Stanley S (2005). Helicopters: An Illustrated History of Their Impact. Santa Barbara, CA: ABC-CLIO. ISBN 1-85109-468-7.
  • Taylor, John W.R. (1960). Jane's All the World's Aircraft 1959-1960. London: Sampson Low, Marston & Co. ASIN B002G60XF8.
  • Swanborough, Gordon (1964). Vertical Flight Aircraft of the World. Fallbrook, CA: Aero Publishers. ASIN B009FNYH16.
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