|Role||Single-engine utility aircraft|
|National origin||United States|
|Manufacturer||Kestrel Aircraft Company|
|First flight||19 November 1995|
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. It had a fixed tricycle landing gear and a conventional four-seat cabin layout. 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. A number of improved variants of the KL-1 were planned including an armed observation or forward air control version with underwing weapon pylons. While the prototype was test flying to gain certification the programme was abandoned.
- Baseline four-seat production variant with a 160 hp (119 kW) Lycoming O-320-D2G piston engine, one built.
- Proposed de-luxe four-seat variant with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.
- Proposed high-performance variant with a 160 hp (119 kW) Continental IO-520 piston engine, not built.
- 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.
- Proposed retractable landing gear variant of the KL-1B with a 190 hp (142 kW) Lycoming IO-360-ES piston engine, not built.
- Proposed military armed observation or forward area control variant of the KL-1C with additional observation windows and underwing weapons pods, not built.
Data from Jane's All the World's Aircraft 1995-1996
- 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)
- 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)
- Aircraft of comparable role, configuration and era
- Jackson 1995, p. 546