Dova Aircraft

DV-1 Skylark

DV-1 Skylark is an ultralight, single-engine, two-seater, low-wing aircraft with a fixed tricycle undercarriage.


The aircraft is combination of primary classic anti-corrosion all-metal construction which is riveted and bonded and composite parts to achieve elegant external contours. The DV-1 aircraft is designed to be used for flight training, glider towing and recreational flights. Pilots will appreciate not only the roomy cockpit space and comfortable ergonomic seats but also the precise aerodynamics of the aircraft.

The aircraft meets the requirements of ASTM, FAA and is certified under Czech LAA and German DULV. Operation of the aircraft is assumed only during the day under VFR rules under VMC conditions.

Dova Aircraft Skylark DV-1

Ten steps to perfection

Modern technology, precise design, maximum emphasis placed on safety and passion for flying. All this manifests our aircrafts.

1
Elegant fuselage

  • Semi-monocoque construction formed with reinforcements and duralumin skins.
  • All structural parts are from duraluminium.
  • The tail fin is an integral part of the fuselage.
  • Control system welded parts are made from strength aviation steel L-CM3.3.
  • Engine compartment is separated by stainless steel fireproof wall from cockpit.

2
Trapezoid semi-monocoque wing

  • Equipped with ailerons and flaps with simple folding system assuring durable and reliable function and winglets made from fiberglass installed for better climbing performance.
  • The wing is designed as self-supporting construction with main and auxiliary spars.
  • Attached through three hinges into fuselage.
  • The airfoil shape is formed by duralumin hardened leading and trailing edge ribs finally skinned with duralumin sheets.

3
Vertical and horizontal tail units (VTU, HTU)

  • Semi-monocoque structure of vertical and horizontal tail assemblies consists of ribs, beams and stressed skin.
  • The shape of the HTU is rectangular.
  • The T-tail conception consists of rudder, stabilizer and elevator with an electric trim tab.
  • The rudder is attached to the fin part by two hinges.

4
Landing gear with nose wheel

  • The front steerable leg is made from steel tube and rubber shock absorbers.
  • The main undercarriage legs are composed of a fiberglass springs.
  • Wheels on both undercarriage legs are standardly equipped with 14x4 tires.
  • Hydraulic disc brakes, controlled by toe brake pedals on the rudder pedals.
  • Each hydraulic brake is controllable separately so it gives together with a steerable nose wheel, easy taxiing of the aircraft on the ground.

5
Effective dual control system

  • The ailerons and elevator are controlled by control sticks, connecting push-pull rods and bell cranks.
  • The rudder is controlled by pedals and cables.
  • Geometry of toe-brake pedals is improved to minimize possible unintentional braking.
  • The flaps are controlled mechanically; the flaps control lever is located between the seats.
  • The elevator trim tab is standardly electrical, operated by a trim controll switch located on the instrument panel.

6
Power plant Rotax

  • Two options of engine Rotax available – 912 UL (80 HP) / 912 ULS (100HP)
  • The engine is attached to the engine bed which is suspended on the firewall.
  • The cylinder heads are liquid cooled, and the cylinders are air cooled.
  • Dry-sump forced lubrication system.
  • Dual-electronic ignition.
  • Engine equipped with electric starter, AC generator and the mechanical fuel pump.

7
Sophisticated fuel system

  • Fuel system consists of two wing integral tanks in total amount 90 liters (23,8 US gal), a fuel tank selector, a filter and a fuel pump on the engine.
  • Each tank has a vent, drain valve fuel meter and filter in outlet valve.
  • Fuel system consist a three way fuel selector valve in fuselage and fine fuel filter in engine compartment.
  • The installation of electric fuel pump, fireproof sleeves for hoses or equip fuel tanks with lockable fuel caps is possible on request.

8
Aircraft electrical system

  • With negative pole separated by grounding points connected to the battery.
  • The system is protected by the circuit breakers placed on the main switch panel.
  • As a power source serve the single-phase generator integrated to the engine and the 12V maintenance less battery located on the firewall.

9
Aerodynamically fitted cockpit canopy

  • Two-man crew cockpit accessible after opening the one-part perspex overlap canopy.
  • Side-by-side fixed thin-cushioned ergonomic seats with reliable safety seat belts.
  • The baggage compartment is located behind the backrests and is designed for maximum of 20 kg (44 lbs) load.
  • The canopy is equipped with a latch locking mechanism.
  • Efficient cockpit ventilation through the eyeball vents is connected to the NACA scoops.
  • The heating system with separate regulation of warm and cold air volume and air distribution. Windshield defrost and demist system, is safe for taxiing.

10
Pitot-static system

  • Pressure distribution to individual instruments is done through flexible plastic hoses.

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Weights and loading

Ultralight E-LSA
Empty weight 287 kg 290 kg
Maximum take-off weight 450 kg (472.5 kg w/rescue system) 600 kg
Useful load 163 kg 310 kg
Fuel tanks capacity 90 l 90 l
Maximum baggage weight 20 kg 20 kg
Load factors in g’s (+4, -2) (+4, -2)

Operational speeds

Ultralight E-LSA
Stall speed without flaps 78 km/h 83 km/h
Stall speed with flaps 64 km/h 68 km/h
Never exceeded speed 267 km/h 267 km/h
Maximum horizontal flight speed 230 km/h 230 km/h
Travel speed 210 km/h 210 km/h
Climb rate 6 m/s 5.9 m/s
Ceiling 3650 m 3650 m
Range (30 min. reserve) 1000 km 900 km

Aircraft dimensions

Wing span 8.14 m
Aircraft lenght 6.62 m
Aircraft height 2.28 m
Cabin width 1.09 m
Wing area 9.44 m2
Horizontal tailplane surface 1,48 m2
Vertical tailplane surface 0.9 m2

Other parameters

Cruise speed at 3000 ft with 75 % of power 210 km/h
Maximum horizontal flight speed 230 km/h
Take-off distance to 50 ft (15 m): concrete 265 m
Take-off distance to 50 ft (15 m): grass 280 m
Braking distance 153 m
Range (30 min. reserve) 1000 km
Endurance 5 h
Fuel capacity 90 l
Average fuel consumption 15 l/h