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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 Type of 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)

See also

Aircraft of comparable role, configuration, and era

• Cessna 172

References

Notes

Bibliography

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