Structure: shoulder-wing single seater of a classical layout, designed in accordance with the requirements of JAR-22, U Category. The glider's life should be 9,000 flight hours (20 years). Airplane or winch launching can be used, another option is a bungee catapult.

Wing: The profile, referred to as NN 18-17, has relative thickness of 17%. It features high c_z coefficient and is insensitive to dirt. The wing has a straight taper with rounded swept-back tips, the airbrakes on the upper surface and conventional ailerons. Wings are mono spar construction with sandwich skin filled with hard PVC foam. The left and right spars are identical. Wings are rigged to the fuselage with the use of two transverse pins. At the ends of wings small nylon wheels are installed.

Fuselage: The fuselage shape is the result of optimization: utmost safety of take-off and landing (including bungee catapult release), good performance at low flying speed, easy ground handling. The fuselage skins and vertical stabilizer are molded in one-piece halves and joined together in the plane of symmetry. The fuselage laminar coats are strengthened with fabrics. The two main metal-composite wing spars have identical metal ferrous connecting them of organic glass and opening forward. The pilot's seat is reclining with space for a ballast in order to obtain maximum weight irrespective of the pilot's weight.

Tail unit: A typical tail unit has been used as it is characterized by simple construction and low weight. Then horizontal tail unit is molded in one piece and connected to the fuselage at three points. The elevator unit hooks up automatically on assembly. Composite tail and elevator unit are strengthened with fabrics.

Landing gear: Landing gear is two-wheel tandem type. The main wheel (300 mm) is located behind the center of gravity. It is equipped with a brake and an efficient rubber shock absorber and suspended on a balance lever. The tail support with additional small wheel.

Controls: All metal construction designed in accordance with sailplane standards. The elevator control, aerodynamic brakes and ailerons are pusher type. Rudder control-cable type. Typically located standard control system (stick and pedals). Pedals can be adjusted during flight. All controls are automatically connected during assembly.

Equipment: two types instrument panels are available: standard and  competition. In both case are fitted with basic glider instruments: van-type rate of climb indicator, total energy compensator, barometric altimeter, air speed indicator, second rate of climb indicator, electrical turn and bank indicator and magnetic compass. Glider is equipped with two hooks for aero tow and for winch launching.