Kestrel KL-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.

KL-1
Role Single-engine utility aircraft
National origin United States
Manufacturer Kestrel Aircraft Company
First flight November 19, 1995
Number built 3

Design and development

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
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 250 hp (186 kW) Continental TSIO-360C piston engine, 2 built.[1][2]
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)

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 sq ft (16.69 m2)
  • Empty weight: 1,375 lb (624 kg)
  • Gross weight: 2,500 lb (1,134 kg)
  • Powerplant: 1 × Lycoming O-320-D2G four-cylinder piston engine. , 160 hp (119 kW)

Performance

  • Cruise speed: 143 mph (230 km/h, 124 kn)
  • Stall speed: 54 mph (87 km/h, 47 kn)
  • Range: 1,088 mi (1,752 km, 945 nmi)
  • Service ceiling: 13,000 ft (3,965 m)
  • Rate of climb: 700 ft/min (3.6 m/s)
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gollark: It's amazing how easy it is to *not* waste millions of RF/t somehow.
gollark: The large and small whiteish towers actually have basically nothing in them now.
gollark: My crazily convoluted base so far.
gollark: I'll make an AE2 one if I figure out the fundamental problem of "where in the base does this go?"

See also

Aircraft of comparable role, configuration and era

References

Notes
  1. Jackson 1995, p. 546
  2. Eckland, K.O. "Aircraft K". Aerofiles. Retrieved 13 October 2017.

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