Kestrel KL-1

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Kestrel KL-1
Role Single-engine utility aircraft
National origin United States
Manufacturer Kestrel Aircraft Company
First flight 19 November 1995
Number built 1

The Kestrel KL-1 is an American single-engined four-seat utility aircraft designed and built in the 1990s by the Kestrel Aircraft Company of Norman, Oklahoma.

Design and development[edit]

The KL-1 is a composite fuselage cantilever high-wing cabin monoplane designed to meet the requirements of the utility and normal categories of Part 23 of the Federal Aviation Regulations.[1] It had a fixed tricycle landing gear and a conventional four-seat cabin layout.[1] The prototype designated KL-1A and registered N960KA first flew on 19 November 1995 and was powered by a 160 hp (119 kW) Lycoming O-320-D2G piston engine driving a two-bladed fixed pitch propeller.[1] A number of improved variants of the KL-1 were planned including an armed observation or forward air control version with underwing weapon pylons.[1] While the prototype was test flying to gain certification the programme was abandoned.

Variants[edit]

KL-1A
Baseline four-seat production variant with a 160 hp (119 kW) Lycoming O-320-D2G piston engine, one built.[1]
KL-1B
Proposed de-luxe four-seat variant with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.[1]
KL-1C
Proposed high-performance variant with a 160 hp (119 kW) Continental IO-520 piston engine, not built.[1]
KL-1D
Proposed six-seat utility and cargo variant with a 325 hp (242 kW) Continental TSIO-550-B engine, and an optional floatplane conversion, not built.[1]
KL-1R
Proposed retractable landing gear variant of the KL-1B with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.[1]
K250A
Proposed military armed observation or forward area control variant of the KL-1C with additional observation windows and underwing weapons pods, not built.[1]

Specifications (KL-1A)[edit]

Data from Jane's All the World's Aircraft 1995-1996

General characteristics

  • Crew: 1
  • Capacity: 3
  • Length: 26 ft 9 in (8.15 m)
  • Wingspan: 36 ft 9 in (11.20 m)
  • Height: 8 ft 11 in (2.73 m)
  • Wing area: 179.6 ft2 (16.69 m2)
  • Empty weight: 1375 lb (624 kg)
  • Gross weight: 2500 lb (1134 kg)
  • Powerplant: 1 × Lycoming O-320-D2G four-cylinder piston engine., 160 hp (119 kW)

Performance

  • Cruise speed: 143 mph (230 km/h)
  • Stall speed: 54 mph (87 km/h)
  • Range: 1088 miles (1752 km)
  • Service ceiling: 13000 ft (3965 m)
  • Rate of climb: 700 ft/min (3.6 m/s)

See also[edit]

Aircraft of comparable role, configuration and era

References[edit]

Notes[edit]

  1. ^ a b c d e f g h i j Jackson 1995, p. 546

Bibliography[edit]

  • Paul Jackson, ed. (1995). Jane's All the World's Aircraft 1995-1996. Jane's Information Group Limited. ISBN 0-7106-1262-1.