“Sawyer Skyjacker II”的意思、由来-开放百科全书

The Sawyer Skyjacker II is an American homebuilt aircraft that was designed and produced by Ralph V. Sawyer of Lancaster, California, in 1974. The aircraft was intended as a research project and as such only one was built.^[1]

Design and development

The Skyjacker II was designed to explore ultra-low aspect ratio wing designs and in particular the stability, controllability and capability of the configuration. The design was intended to be easily scalable to much larger aircraft. It has no complex curves and was designed to be easy to construct. It features a cantilever mid-wing, a two-seats-in-tandem enclosed cockpit under a glazed canopy, fixed tricycle landing gear with wheel pants and a single engine in pusher configuration.^[1]

The aircraft is made from sheet aluminum, has an {{convert|18.0|ft|m|1|abbr=on}} span wing and is powered by a {{convert|200|hp|kW|0|abbr=on}} Lycoming IO-360-A1B6D engine. The aircraft has an empty weight of {{convert|1650|lb|kg|abbr=on}} and a gross weight of {{convert|2250|lb|kg|abbr=on}}, giving a useful load of {{convert|600|lb|kg|abbr=on}}. With full fuel of {{convert|50|u.s.gal}} the payload is {{convert|300|lb|kg|abbr=on}}.^[1]^[2]

The aircraft proved to be stall and spin proof. Its standard day, sea level take off run is {{convert|1200|ft|m|0|abbr=on}} and landing roll is {{convert|1000|ft|m|0|abbr=on}}.^[1]

The sole example built was registered in the United States with the Federal Aviation Administration in 1974, but its registration was cancelled in August 2013.^[3]

Specifications (Skyjacker II)

|genhide=
|crew=one
|capacity=one passenger
|length m=
|length ft=18
|length in=0
|length note=
|span m=
|span ft=18
|span in=0
|span note=
|height m=
|height ft=
|height in=
|height note=
|wing area sqm=
|wing area sqft=
|wing area note=
|aspect ratio=
|airfoil=
|empty weight kg=
|empty weight lb=1650
|empty weight note=
|gross weight kg=
|gross weight lb=2250
|gross weight note=
|fuel capacity={{convert|50|u.s.gal}}
|more general=

|perfhide=
|max speed kmh=
|max speed mph=130
|max speed kts=
|max speed note=
|cruise speed kmh=
|cruise speed mph=105
|cruise speed kts=
|cruise speed note=
|stall speed kmh=
|stall speed mph=45
|stall speed kts=
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range km=
|range miles=
|range nmi=
|range note=
|endurance=
|ceiling m=
|ceiling ft=
|ceiling note=
|g limits=
|roll rate=
|glide ratio=
|climb rate ms=
|climb rate ftmin=400
|climb rate note=
|time to altitude=
|sink rate ms=
|sink rate ftmin=
|sink rate note=
|lift to drag=
|wing loading kg/m2=
|wing loading lb/sqft=
|wing loading note=
|power/mass=
|thrust/weight=
|more performance=
|avionics=
}}

References

1. ^¹²³⁴Plane and Pilot: 1978 Aircraft Directory, page 152. Werner & Werner Corp, Santa Monica CA, 1977. {{ISBN|0-918312-00-0}}
2. ^{{Cite web|url = http://aerofiles.com/_sa.html|title = American airplanes: Sa - Si |accessdate = 18 October 2013|last = Aerofiles|year = n.d.}}
3. ^{{cite web|url = http://registry.faa.gov/aircraftinquiry/NNum_Results.aspx?NNumbertxt=7317|title = N-Number Inquiry Results - N7317|accessdate = 18 October 2013|last = Federal Aviation Administration|date = 18 October 2013}}

External links

5 : Sawyer aircraft|United States experimental aircraft 1970–1979|Single-engined pusher aircraft|Mid-wing aircraft|Homebuilt aircraft