High Performance | Payload | Economical | Comfort at lowest possible price



The main SD-2 mission is fast cross country flying in the very comfortable way. The spacious cockpit with highly inclined seat rests, sufficient shoulder room and adjustable pedals allows long flights without excessive fatigue even for tall pilots. Those who want to use fully this SD-2 advantage choose in flight variable propeller which assures economic cruise speed of 230 km/h (125 kts ) at 65% power setting.
The SD-2 is not only fast but has also precise and harmonic controls so is real pleasure to fly it. It is also great plane for short sightseeing flights when you want to show broad vicinity of airport to your friends.


SD-2 SpecificationSI UnitsImperial Units
Wingspan8.7 m28.71 ft
Length5.8 m19.14 ft
Wing area9.1 m298 ft2
Cabine width1.17 m3.9 ft
Empty weight270 kg600 lbs
MTOW472.5/600 kg1050/1333 lbs
Fuel tank capacity2x50 l2×13.2 US gal
Limit loads+4/-2g
Ultimate loads +7.5/-3.75 g
SD-2 Performance for MTOM=600 kgSI UnitsImperial Units
Stall speed no flaps VS197 km/h61 mph
Stall speed with flaps VSO72 km/h45 mph
Design manouvering speed VA195 km/h121 mph
Max. speed in rough air VRA (65% power setting with the R912 ULS+variable pitch prop)
240 km/h150 mph
Never exceed speed VNE288 km/h180 mph

The SD-2 SportMaster is two seat light airplane in side by side order. It is designed in accordance to LTF-UL/UL-2 regulations but could be operated also as LSA or Experimental airplane. The main emphasize was given on high performance + payload + comfort at lowest possible price.


The fuselage is of wood truss design with prevalent section 15×15 mm covered with plywood of 1.5-3 mm thickness. The pilot seat back is inclined under 37°. Both seats are equipped with in flight adjustable pedals with 150 mm range.  These assure comfort also for 200 cm (6.6 ft) tall pilot. The inside width of cockpit in shoulder place is 117 cm (46″). The plywood tunnel with wing and main gear legs mounts is under pilot knees. The baggage compartment of 190 l (6.7 cb ft) volume and 30 kg/66 lbs  capacity is behind seats. The optional parachute rescue system container is placed in front of instrument panel.


Two half wing uses GA 37U-A315 airfoil. It consists of full carbon composite main spar with caps from the pultruded profiles. The integral fuel tank made of composite sandwich and XPS ribs are glued to the main spar.   The rest of wing is covered with 1.5 mm plywood. Wingtips are made of glass/PVC foam sandwich. Big and efficient slotted flap is made of carbon/PVC foam sandwich. The staticaly counterbalanced ailerons are of plywood/XPS foam construction. Connection of wings to fuselage is performed thru two main and two auxiliary pins.  Disassembly of wings from fuselage takes 10 min and assembly 15 minutes.




The all movable horizontal tail (HT) has electrically actuated anti-servo/trim tab and is statically balanced. Tails are of similar construction as wings- on composite spar are attached polystyrene ribs and plywood skin. Disassembly of HT is made thru disconnection of control and tab rods and pulling out of pin. The fin has main composite spar with carbon caps and HT hinge.


The tricycle undercarriage has controllable nose gear of 300 mm DIA. The main wheels of 350 mm DIA are mounted on cantilever glass composite legs. Hydraulic brakes are actuated by lever on the middle console. The parking brake switch is installed behind the brake lever.


The horizontal tail and ailerons are controlled via pushrods and bell cranks. The rudder is controlled via cables. Flaps are actuated mechanically via lever on middle console. The electricaly actauted flaps are an option.


It is possible to use any engine of 65-120 HP power range up to 110 kg (243 lbs) weight. The production planes are powered by the R 912 engines serie. The R914 powered version is in developement.