“Kestrel KL-1”的意思、由来-开放百科全书

词条

Kestrel KL-1

释义

Design and development
Variants
Specifications (KL-1A)
See also
References
Notes Bibliography

name= KL-1

image= File:Kestrel KL-1A N960KA.jpg

caption=

}}{{Infobox aircraft type

type= Single-engine utility aircraft

national origin= United States

manufacturer= Kestrel Aircraft Company

designer=

first flight= November 19, 1995

introduced=

retired=

status=

primary user=

number built= 3

developed from=

variants with their own articles=
}}

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

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 {{convert|160|hp|kW|0|abbr=on}} 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.

Variants

KL-1A

Baseline four-seat production variant with a {{convert|160|hp|kW|0|abbr=on}} Lycoming O-320-D2G piston engine, one built.

KL-1B

Proposed de-luxe four-seat variant with a {{convert|190|hp|kW|0|abbr=on}} Lycoming IO-360-ES piston engine, not built.

KL-1C

Proposed high-performance variant with a {{convert|250|hp|kW|0|abbr=on}} Continental TSIO-360C piston engine, 2 built.^[1]

KL-1D

Proposed six-seat utility and cargo variant with a {{convert|325|hp|kW|0|abbr=on}} Continental TSIO-550-B engine, and an optional floatplane conversion, not built.

KL-1R

Proposed retractable landing gear variant of the KL-1B with a {{convert|190|hp|kW|0|abbr=on}} Lycoming IO-360-ES piston engine, not built.

K250A

Proposed military armed observation or forward area control variant of the KL-1C with additional observation windows and underwing weapons pods, not built.

Specifications (KL-1A)

{{aerospecs
|ref=Jane's All the World's Aircraft 1995-1996
|met or eng?=eng
|genhide=
|crew=1
|capacity=3
|length m=8.15
|length ft=26
|length in=9
|span m=11.20
|span ft=36
|span in=9
|height m=2.73
|height ft=8
|height in=11
|wing area sqm=16.69
|wing area sqft=179.6
|empty weight kg=624
|empty weight lb=1375
|gross weight kg=1134
|gross weight lb=2500
|eng1 number=1
|eng1 type=Lycoming O-320-D2G four-cylinder piston engine.
|eng1 kw=119
|eng1 hp=160
|eng2 number=
|eng2 type=
|perfhide=
|max speed kmh=
|max speed mph=
|cruise speed kmh=230
|cruise speed mph=143
|stall speed kmh=87
|stall speed mph=54
|range km=1752
|range miles=1088
|ceiling m=3965
|ceiling ft=13000
|climb rate ms=3.6
|climb rate ftmin=700
}}

References

Notes

1. ^{{cite web|last1=Eckland|first1=K.O.|title=Aircraft K|url=http://aerofiles.com/_k.html|website=Aerofiles|accessdate=13 October 2017}}

Bibliography

{{cite book |editor=Paul Jackson |title= Jane's All the World's Aircraft 1995-1996|year=1995 |publisher=Jane's Information Group Limited|isbn= 0-7106-1262-1}}

4 : United States civil utility aircraft 1990–1999|High-wing aircraft|Single-engined tractor aircraft|Aircraft first flown in 1995

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