“Bagalini Bagalini”的意思、由来-开放百科全书

The Bagalini Bagalini is an Italian homebuilt ultralight aircraft that was designed by Marino Bagalini. The aircraft is supplied in the form of plans for amateur construction.^[1]

Design and development

The Bagalini was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of {{convert|254|lb|kg|0|abbr=on}}. The aircraft has a standard empty weight of {{convert|254|lb|kg|0|abbr=on}}.

The aircraft features a strut-braced parasol wing, a single-seat open cockpit without a windshield, fixed tricycle landing gear and a single engine in pusher configuration.^[1]

The Bagalini's fuselage is made from wood and metal, while the wings are a wooden frame covered in doped aircraft fabric. The rear fuselage consists of two tubes, one above and one below the pusher engine. Its {{convert|10.7|m|ft|1|abbr=on}} span wing employs a modified NACA 63-215 airfoil at the wing root transitioning to a NACA 4412 at the wing tips. The wing has an area of {{convert|14.2|m2|sqft|abbr=on}} and is supported by "V" struts. The acceptable power range is {{convert|35|to|40|hp|kW|0|abbr=on}} and the standard engines used are the {{convert|35|hp|kW|0|abbr=on}} Rotax 377 and the {{convert|40|hp|kW|0|abbr=on}} Rotax 447 two-stroke powerplants.^[1]^[2]

The aircraft has an empty weight of {{convert|115|kg|lb|abbr=on}} and a gross weight of {{convert|200|kg|lb|abbr=on}}, giving a useful load of {{convert|89|kg|lb|abbr=on}}. With full fuel of {{convert|11|l}} the payload is {{convert|81|kg|lb|abbr=on}}.^[1]

The manufacturer estimates the construction time from the supplied plans as 700 hours.^[1]

Specifications (Bagalini)

|genhide=
|crew=one
|capacity=
|length m=
|length ft=21
|length in=0
|length note=
|span m=
|span ft=35
|span in=0
|span note=
|height m=
|height ft=
|height in=
|height note=
|wing area sqm=
|wing area sqft=153
|wing area note=
|aspect ratio=
|airfoil=Root: modified NACA 63-215; Tip: NACA 4412
|empty weight kg=
|empty weight lb=254
|empty weight note=
|gross weight kg=
|gross weight lb=450
|gross weight note=
|fuel capacity={{convert|11|l}}
|more general=

|perfhide=
|max speed kmh=
|max speed mph=60
|max speed kts=
|max speed note=
|cruise speed kmh=
|cruise speed mph=40
|cruise speed kts=
|cruise speed note=
|stall speed kmh=
|stall speed mph=27
|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=100
|range nmi=
|range note=
|endurance=
|ceiling m=
|ceiling ft=
|ceiling note=
|g limits=+7/-3.5
|roll rate=
|glide ratio=
|climb rate ms=
|climb rate ftmin=1200
|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=2.9
|wing loading note=
|power/mass=
|thrust/weight=
|more performance=
|avionics=
}}

References

1. ^¹²³⁴⁵Purdy, Don: AeroCrafter - Homebuilt Aircraft Sourcebook, Fifth Edition, page 126. BAI Communications, 15 July 1998. {{ISBN|0-9636409-4-1}}
2. ^¹{{Cite web|url = http://www.ae.illinois.edu/m-selig/ads/aircraft.html|title = The Incomplete Guide to Airfoil Usage |accessdate = 12 December 2013|last = Lednicer |first = David |year = 2010}}