EV-97 Eurostar (Evektor - Aerotechnik)

EV-97 Eurostar is an ultralight aerodynamically controlled airplane intended especially for tourist and free-time flying with the limitation to non-aerobatic operation.

EV-97 EUROSTAR is a single-engine whole-metal low-wing airplane of a semimonocoque structure with two side-by-side seats. The airplane is equipped with the fixed three-wheel landing gear with the controllable nose wheel.

Power unit standardly constists of the four-cylinder four-stroke engine Rotax 912 (80 HP) and the fixed wooden two-blade propeller V 230 C. Alternatively it is possible to install Rotax 912 ULS (S) (having power of 100 HP), Jabiru 2200 A (80 HP) and other propellers according to the customer's wish.

The all-metal airframe of EV-97 Eurostar consists of metal stiffeners, frames and duralumin sheet skin. Parts are mostly joint by pop rivets and by adhesive bonding. Some of parts, especially those parts non-carrying high loads, are made of fibreglass.

The fuselage is of semi-monocoque structure consisting of stiffeners and duralumin skin. The fuselage section is rectangular in the lower part and elliptical in the upper part. The fin is an integral part of fuselage. The cockpit for two-member crew is situated in the middle part of the fuselage and is accessible after folding down the single-part organic glass canopy. The engine compartment in the front part of fuselage is separated from the passenger compartment by the fire wall to which the engine mount is attached.

The wing of rectangular shape is of single spar structure with the auxiliary spar on which ailerons and split flaps are hinged. Riveting is used to assemble all individual design parts. Fiberglas wing tips are riveted on the wing ends. At the customer's wish the airplane can be equipped with the wing folding mechanism, which enables hangaring with minimum room requirements.

Each half of wing is equipped with the rectangular aileron. The aileron consists of ribs and skin, creating cavity. The aileron is hinged on the wing by means of the swivel throughout its length.

Each half of wing is equipped with the split flap that takes about two thirds of half span of wing. The rectangular flap consists of ribs and skin, creating cavity. The flap is hinged on the wing by means of swivel throughout its length.

Horizontal Tail Unit
Horizontal tail unit, of usual type, consists of the stabilizer and the elevator with the trim tab. Single spar structure HTU of rectangular contour is composed of duralumin ribs, spar and skin. HTU span is 2.5 m, which enables transportation of HTU on the trailer without its disassembling.

The rectangular stabilizer consists of ribs and duralumin skin. The stabilizer is attached to the fuselage by shifting on two pins in the front part and is secured by two bolts in the rear part.

The elevator consists of ribs and duralumin skin. The elevator is hinged on the stabilizer by means of swivel. The trim tab is hinged on the trailing edge of the elevator by means of swivel.

Trim Tab
The elevator is equipped with one rectangular trim tab. The trim tab consists of duralumin skin creating cavity. The trim tab makes up about two thirds of HTU and is hinged on the elevator by means of swivel throughout its length.

Vertical Tail Unit
The trapezoidal VTU of rectangular contour consists of the fin and the rudder.

The fin part of VTU is an integral part of the fuselage. Its structure is composed of two duralumin spars, root rib, end rib and skin. The upper part of fin is closed by the laminate cover on which the anti-collision beacon can be installed. The fairing between the fuselage and the tail unit is made by the fibreglass cover.

The trapezoidal rudder is composed of the duralumin spar, skin, upper and lower rib. The rudder is attached to the fin by means of two hinges. The upper part of the rudder is closed by the fibreglass wing tip.

wing span
wing area
empty weight
useful load
gross weight
fuel capacity
Rotax 912, 80HP
5.98 m 
2.34 m
8.10 m
9.84 m2
262 kg

450 kg
70 L
800 km


takeoff distance, ground roll
rate of climb
max speed
cruise speed
landing distance, ground roll
service ceiling
145 m
5.5 m/s
225 km/h
180 km/h
90 m
5000 m

limiting and recommended speeds

design manoeuvring speed (Va)
never exceed speed (Vne)
stall, power off (Vsl)
landing approach speed
270 km/h

All specifications are based on manufacturer's calculations