- Design and development
- Specifications
- References
| name=GY-120 | image= | caption= }}{{Infobox Aircraft Type | type=Two seat ultralight | national origin=France | manufacturer=Société des Avions Yves Gardan | designer=Yves Gardan | first flight=27 April 1984 | introduced= | retired= | status= | primary user= | more users= | produced= | number built=1 | program cost= | unit cost= | developed from= | variants with their own articles=
}} |
The Gardan GY-120 was a single engine, parasol wing ultralight seating two in tandem, designed and built in France in the 1980s. It did not go into production. Design and developmentDesign work on the GY-120, Yves Gardan's first ultralight, began in June 1982. The prototype was built that October and appeared, unflown, at the Paris Air Show of 1983. It flew for the first time on 27 April 1984. The GY-120 had an aluminium alloy tube structure, stressed to FAR 23 standard. Its parasol wing was unswept and of constant chord, carrying half span ailerons. The wing was supported from below by a fore and aft pair of inverted V-form struts from the upper fuselage longerons to the its centreline. These struts also supported a longitudinal inverted V kingpost to which landing wires were attached. Flying wires braced the wing from below to the lower fuselage. The fuselage was flat sided, the fin and rudder straight edged. The leading edge of the fin was swept and the deep, almost rectangular rudder reached down between the elevators, mounted on the tailplane at the top of the fuselage, to the keel. Two seats in tandem were placed below the wing in a continuous open cockpit. The GY-120 had a fixed conventional undercarriage, with the mainwheels on half axles and radius arms mounted on the fuselage centreline and near vertical rubber compression legs fixed to the fuselage sides. The mainwheels had brakes and the tailwheel was coil sprung. The only GY-120 built was powered by a 30 kW (40 hp) Hirth 270 two-cylinder inline, two-stroke engine, though it was designed to accept a variety of engines in the 26-45 kW (35-60 hp) range. Specifications{{Aircraft specs
|ref=Ultralight and Microlight Aircraft of the World
|prime units?=met
|genhide=
|crew=
|capacity=two
|length m=5.80
|length note=
|span m=10.00
|height m=2.50
|height ft=
|height in=
|height note=
|wing area sqm=17.5
|wing area note=
|aspect ratio=5.7
|airfoil=
|empty weight kg=145
|empty weight note=
|gross weight kg=
|gross weight lb=
|gross weight note=
|max takeoff weight kg=340
|max takeoff weight note=
|fuel capacity=30 L (7.9 US gal; 6.6 Imp gal)
|more general=
|eng1 number=1
|eng1 name=Hirth 270R-03E
|eng1 type= air cooled, twin cylinder inline two stroke
|eng1 hp=40
|eng1 note=at 7,000 rpm, toothed belt 2.7:1 output speed reduction
|power original=
|more power=
|prop blade number=2
|prop name=
|prop dia ft=4
|prop dia in=7
|prop dia note=
|perfhide=
|max speed kmh=120
|max speed note=
|cruise speed kmh=75
|cruise speed note=economic
|stall speed kmh=38
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|minimum control speed kmh=
|minimum control speed mph=
|minimum control speed kts=
|minimum control speed note=
|range km=400
|range note=at average cruising speed
|ferry range km=
|ferry range miles=
|ferry range nmi=
|ferry range note=
|endurance=
|ceiling m=2500
|ceiling note=service
|g limits=+6.6/-3.3 ultimate
|roll rate=
|glide ratio=power off 10:1 at 65 km/h (40 mph)
|climb rate ms=2.5
|climb rate note=maximum at sea level
|time to altitude=
|sink rate ms=1.8
|sink rate note=minimum at 65 km/h
|lift to drag=
|wing loading kg/m2=19.4
|wing loading note=maximum
|power/mass=11.4 kW/kg (18.8 hp/lb) maximum at MTOW
|more performance=
- Take-off distance: 40 m (130 ft)
- Landing distance: 35 m (115 ft)
|avionics=
}}{{aircontent
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}}References{{commons category|Gardan}}
}}{{Gardan aircraft}} 5 : French sport aircraft 1980–1989|Aircraft manufactured in France|Parasol-wing aircraft|Single-engined tractor aircraft|Aircraft first flown in 1984 |