The Vagabond Family of new aircraft



The Etruria E200 Vagabond



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