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General .
Maximum visibility like
an helicopter. Ease of maintenance and
disassembly, low cost, little sensitive to air turbulence, high
internal comfort, large baggage comportment..
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Wing.
Un-braced high wing,
VG1-13H high lift airfoil designed
for the G97, constant chord, dihedral 1°, incidence 2°.30’, no twist, wing
detachable
for storage and transportation, integral leading edge fuel tank (2x35
litres).
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Fuselage
Large transparent nose
section with two large transparent doors, rear nacelle for engine
installation behind the wing (pusher propeller).
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Flying controls.
Full dual controls and
one central throttle, differential Frise
ailerons, stabilator tailplane
with anti-balance/trim tab, electrically actuated trim tab and slotted
flaps covering 71% of wing span.
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Structure.
All-metal basic structure
of aeronautical aluminium alloy except tailplane
and rudder, Dacron covered,and wing-fuselage
fairing, wing and vertical fin tips, engine nacelle and tail
cone which are of Fiberglas.
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Lauding gear.
Fixed tricycle,
hydraulic disk brakes, nose wheel with rubber shock-absorber.Main
gear in one spring of carton-Fiberglas, mounted under the
fuselage structure with four bolts for easy disassembly.
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Power plant.
One 80 hp Rotax 912 (*), four-cylinder four-stroke liquid/air
cooled engine.
Propeller of maximum diameter of 172 cm .
Basic version: Tonini propeller 166cm/145cm
diameter to pitch ratio.
(*) Rotax 912 of 100 hp is foreseen.
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Accommodation.
Side-by-side
adjustable seats with four point harness.
Large baggage spaces behind seats: one of about 0.8x0.8x0.45 cub.m. and one og about 0,3x0.8x0.3 cub.m.
Two small compartments for documents and objects closed by doors in
lateral panels of baggage comportment.
Cabin floor as high as 0.6
m above the ground for an easy accommodation.
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Systems.
12 V battery;
100 W alternator.
Ram cabin air by adjustable outlets.
Anemometer, altimeter, R/C indicator, bank indicator, trim indicator,
L.H. and R.H. trim position, flap position
indicator, rpm indicator, oil temperature, oil pressure, cooling liquid
temperature indicators, compass,
fuel levels visible.
Optional on
customer specification.
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Fuel tanks.
Two leading edge
integral fuel tank of 2x35 litres of total capability.
Dimensions.
Wing span 8,25
m (27
ft), wing chord constant 1.25 m (4 ft 1 in) Wing aspect ratio
6.6, length overall 6.24 m height overall 2.3 m (7 ft).
Tailplane span 2.9 m (9 ft 6in), wheel track 2.14 m (7 ft), wheel base 1.55 m (5 ft). Cabin max width 1.08 m (3ft 6.5 in).
Areas.
Wings, gross 10.3 sqm. (110,9 sqft). Tailplane 1.97 sqm. (21.2 sqft).
Vertical plane 1.17 sqm. (12.6 sqft).
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Weights.
Basic empty weight
270 to 280 kp.
Maximum weight 450 kp (**) ,
as for italian Ulm
category.
(**) Structure capable of bearing up to 530 kg take off
weight.
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Performances.
Max speed at sea
level 200 km/h (102 kt)
Cruising speed 75% 176 km/h (92 kt)
Stalling speed – flaps retracted 69 km/h (39 kt)
Stalling speed – flaps extended 58 km/h (31 kt)
Max climb rate at sea level : 280 m/min
T.o./ landing run 85 m/85 m
Endurance over 4 h
Load factors: +4/-2.
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Characteristics
of the G97 V Spotter - Certified version.
Certification standard: Italian ENAC V.EL
Configuration, structure, dimensions, power plant idem ULM version.
An increased wing span up to 8.75
m is foreseen to improve the rate of climb.
Same systems and flying controls of the ULM version with the addition of fuel
pressure indicator, fuel auxiliary pump, radio,
stall warning and electrical safety devices.
Optional are customer specification.
Weights.
Empty weight 290 to 300 kp
Maximum weight 530 kp
Performances.
Max speed at sea level 192 km/h (97 kt)
Cruising speed 75% 170 km/h (89 kt)
Stalling speed flaps retreated 76 km/h
Stalling speed flaps extended 63 km/h
Rate of climb at sea level 240 m/min
T.O./Lauding rum 130/110 m
Endurance over 4 h
Load factors: +4/-2
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