All the tail surfaces of the JG.10 were straight tapered with rounded tips and carried unbalanced control surfaces. The tailplane, which had a wooden structure and was ply covered, was built into the fuselage and strut-braced to the fin. The elevators were fabric covered. The high aspect ratio vertical tail comprised a fin, constructed like the tailplane and an all-metal rudder which ended above the elevators.^[2]

The JG.10 had fixed, conventional landing gear, its mainwheels on bent axles with rearward drag struts, all hinged to the central fuselage underside. Vertical oleo struts from the ends of the axles were attached to the forward wing spars; the track was {{convert|3.0|m|in|abbr=on}}.^[2] A vertical tube extending from the extreme rear of the fuselage carried a small castering tailwheel below a shock-absorbing spring. The end of the extension was supported by a small V-strut to the lower fuselage.

Development

The first flight of the Guillemin JG.10 was on 1 June 1931.^[15] In August it was being developed at Villacoublay^[3] whilst also serving as Louis Blériot's transport in the neighbourhood of Paris.^[17] In October it took part in the Concours National d'Avions de Tourisme (National touring aircraft competition), which began at Orly in late September, but had to retire with fuel flow problems.^[18]

The sole JG.10 remained active for six years. It was demonstrated at a civilian pilots' reunion festival at Orly in May 1932^[19] and was back at Villacoublay (with the STIAé) in December,^[20] where it remained until at least May 1934.^[21] In August 1935 it was there once again, test-flying at the Centre d'Essais de Matériels Aériens, Villacoublay.^[22]

It was destroyed in a fatal accident at Villacoublay on 16 June 1937; both crew died. The cause was inflight structural failure which was ascribed to weathering in an aircraft that had been housed for two years at Buc in a hangar partially open to the elements.^[23]

Specifications

|genhide=
|crew=Two
|capacity=
|length m=7.10
|length note=
|span m=13.00
|span note=
|height m=2.20
|height note=
|wing area sqm=23
|wing area sqft=
|wing area note=
|aspect ratio=
|airfoil=
|empty weight kg=554
|empty weight note=equipped
|gross weight kg=850
|gross weight note=
|max takeoff weight kg=
|max takeoff weight lb=
|max takeoff weight note=
|fuel capacity={{convert|130|l|Impgal USgal|abbr=on}}
|more general=

|eng1 number=1
|eng1 name=Renault 4Pb
|eng1 type=air-cooled 4-cylinder inline
|eng1 hp=95
|more power=
|prop blade number=
|prop name=
|prop dia m=
|prop dia ft=
|prop dia in=
|prop dia note=

|perfhide=
|max speed kmh=160
|max speed note=at sea level
|cruise speed kmh=
|cruise speed mph=
|cruise speed kts=
|cruise speed note=
|stall speed kmh=
|stall speed mph=
|stall speed kts=
|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=500
|range note=
|endurance=
|ceiling m=4500
|ceiling note=
|g limits=
|roll rate=
|glide ratio=8
|climb rate ms=
|climb rate ftmin=
|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=
|fuel consumption kg/km=
|fuel consumption lb/mi=
|power/mass=
|thrust/weight=
|more performance=
}}

References