The Three Lifting
Surface Concept
The Etruria E200TC
Vagabond
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Type: The
Etruria 200 Vagabond is the basic version of a family of 4-5 seats,
high performance, touring aircraft, designed to FAR Part 23
regulations. Major design features include the adoption of a
“Three Lifting Surface Configuration (3LSC)” concept,
to reduce cruise drag and fuel consumption, and the placement of
the single engine aft of the fuselage/wing intersection, to
minimize the engine noise level in the passenger cabin. The front
cabin profile has no discontinuity at the windshield intersection.
The main wing mates with the fuselage at a mid-vertical position.
The landing gear retracts into the fuselage contour. Extended
laminar flow on wing and canard surfaces is achieved using
appropriate contours and smooth manufacturing techniques. Advanced
technologies and composite materials are selected for particular
structural components to reduce weight and improve external surface
finishing which contribute to the aerodynamic efficiency at high
speed. Higher cruise speed differentiates this aircraft from all
other aircraft in the same class. This achievement is derived from
the appropriate selection of advanced concepts and technologies
available today. The design of the Vagabond family of aircraft
benefits from the extensive experience achieved from research and
development of the Piaggio P180 Avanti by these same designers.
Wing: The wing is comprised of a three-section structure.
The single center wing section extends between left and right tail
boom intersections and it is permanently mated to the fuselage. The
wing main torsion box is made of graphite epoxy composites.
Integral aluminum leading edges include fuel tank cells. Trailing
edges and flaps are conventional light alloy sheet metal structure.
Outboard sections, left and right, made of graphite composites, are
mated to the center section. Laminar wing sections and external
smooth finishing assure extended laminar flow conditions. Outboard
wing structures support conventional flaps and ailerons.
Canard: The canard is a single structure of graphite epoxy
composites with fixed geometrical incidence to the fuselage. Its
forward sweep of 20 degrees plus 5-degree anhedral geometry is
designed for optimum pilot's vision. The flaps are of light
alloy sheet metal. Close tolerance manufacturing of the entire
structure assures an extended laminar flow.
Horizontal Tail: A single piece, constant section,
conventional light alloy horizontal tail structure is supported at
each end by each of the tail-booms. The single elevator surface
with trim capability incorporating dual elevator control system
provides fail-safe capabilities.
Tail-booms: Two graphite composite tail-booms of fail-safe
design connect the horizontal tail to the main wing structure.
Vertical tails are integral with tail-boom structures.
Fuselage: A mixed construction of aluminum frames and spars
riveted to kevlar/carbon laminated stressed skin forms the
passenger cabin section in front of the main aluminum bulkhead,
which takes the loads from wings and landing gear. This structural
section is permanently mated with the center wing structure.
Entrance doors are located on both sides of the fuselage. A
flush-type, bird-proof windshield assures unobstructed
pilot’s vision. The aft section fuselage structure is of
conventional light aluminum alloy with a composite engine
cowling.
Accommodation: Individual seats are located at each of the
dual controls. Entry is through left and right doors, upward
hinged. The design features a crash resistant cabin structure and
low internal noise level due to the aft mounting of the engine and
its pusher propeller. Behind the rear passenger seats is the
baggage compartment, which is accessible both from the cabin and
the exterior.
Powerplant: Propulsion is from a single flat-six, 210 HP,
Teledyne-Continental IO-360-C, fuel injected, piston engine,
driving a two blade, constant-speed, metal propeller. FADEC and
single lever control are optional. A clamshell cowling arrangement
comprised of two sections opens completely away from and provides
easy access to the engine. Total fuel capacity: 265 liters (70 US
gal)
Landing Gear: Hydraulically retractable tricycle-type
landing gear each retracts into the fuselage contour. Landing gear
doors are made of composite material and are hydraulically
operated.
Dimensions, external:
Wing
Span |
10,00
m
|
32.8
ft
|
Length,
Overall |
7.74
m
|
25.4
ft
|
Height |
2.70
m
|
8.8
ft
|
Dimensions, internal:
Cabin
Length |
3.15
m
|
10.33
ft
|
Max Cabin
Width |
1.32
m
|
4.31
ft
|
Max Cabin
Height |
1.20
m
|
3.93
ft
|
Areas,
gross:
Canard |
1.25 m2
|
13.46
ft2
|
Wing |
8.20
m2
|
88.26
ft2
|
H/tail |
1.50
m2
|
16.15
ft2
|
Weights:
Empty |
817
Kg
|
1800
lb.
|
Max Zero
Fuel |
1249
Kg
|
2750
lb.
|
Max Take
Off |
1317
Kg
|
2900
lb.
|
Landing |
1251
Kg
|
2755
lb.
|
Useful
Load |
499
Kg
|
1100
lb.
|
Max
Payload |
431
Kg
|
950
lb.
|
Max
Fuel |
191
Kg
|
420
lb.
|
Max
Bags |
154
Kg
|
430
lb.
|
Fuel w/ max
Payload |
68
Kg
|
150
lb.
|
Payload w/ max
Fuel |
309
Kg
|
680
lb.
|
|
|
Occupant w/
max Fuel |
4
pass.
|
Performance:
At Sea
Level, MTOW, standard day
Max Level
Speed |
370
Km/h
|
200
Kt
|
Cruise Speed
(75% Power) |
330
Km/h
|
180
Kt
|
Stall Speed,
Flaps Up |
146
Km/h
|
81
Kt
|
Stall Speed,
Full Flaps |
111
Km/h
|
60
Kt
|
At 8000 ft, MTOW,
Standard Day
Max Level
Speed |
268 Km/h
|
185
Kt
|
Cruise Speed
(75% power) |
305
Km/h
|
145
Kt
|
At 12000 ft,
MTOW, Standard Day
Max Level
Speed |
314
Km/h
|
170
Kt
|
Cruise
Speed |
272
Km/h
|
147
Kt
|
VFR Range,
Seat Full, Cruise Speed |
925
Km
|
500
Nm
|
VFR Range,
Full Tanks |
1850
Km
|
1000
Nm
|
|