PW-5 “Smyk” is a shoulder-wing single seater of a clasical layout, designed in accordance with requirements of JAR-22, U Category.The glider’s life should be 9000 flight hours (20 years). For launching, an airplane or a car equipped with a winch can be used. The glider is simple, small and light enough to be rigged and de-rigged easily by two people and stored even in a home garage.

The structure is entirely glass-epoxide composites with chemically hardening binder.

Wings are monospar construction with sandwich skin filled with hard PCV foam, with airbrakes on the upper surface and conventional ailerons.
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 cockpit canopy is one piece structure entirely made 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.
Pedals can be adjusted during flight.
The elevator unit hooks up automatically on assembly.
The landing gear is of two-wheel tandem type. The main is equipped with a brake and an efficient rubber shock absorber and suspended on a balance lever.




BASIC TECHNICAL DATA:

Wing span: 13,44m
Overall lenght: 6,22m
Height: 1,86m
Wing area: 10,16m²
Wing aspect ratio: 17,8
Max. empty weight: 190 kg
Max. take-off weight: 300 kg
Limit load factors for V_A: +5,3 –2,65
Limit load factors for V_NE: +4,0 –1,50

PERFORMANCE:

Gliding ratio:  33
Minimum rate of sink at 73km/h:  0,64m/s
Manoeuvring speed V_A: 147km/h
Never exceed speed V_NE: 220km/h
Stall speed: 58km/h

APPROVED AEROBATIC MANOEUVRES:

   - loop
   - stall turn
   - spin
   - spiral

KINDS OF OPERATIONS:

   - day flying
   - cloud flying
   - earobatics manoeuvres as above

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The PW-6U is a dual-seat sailplane with the cantilever mid wing and standard tailplane arrangement, desinged with accordance with the requirements of JAR-22, U Category. The sailplane has the all epoxy-glass composite structure.

The wings are of trapezoid contour with bow-shaped ends. The wings have mono-spar structure with sandwich shells.
The air brakes are of panel-type extendable form the upper wing surface.
The fuselage shells are of monocoque structure, stiffened with frames.
The rudder is covered with fabric skin.
The forward cockpit is equipped with rudder pedals adjustable in flight and the backrest adjustable on the ground. The canopy opens forward.
Limuzyna przednia otwierana do przodu. 
The rear cockpit is provided with non-adjustable rudder pedals and the backrest adjustable on the ground. The canopy opens aftward.
The sailplane landing gear is not retractable and consists of the main wheel provided with shock absorber and drum brake, nose wheel and tail wheel.
The sailplane is provided with two takeoff hooks (the nose hook is used for aerotowing and the C.G. hook for winch-launching).

BASIC TECHNICAL DATA:

Wing span: 16,00m
Lenght: 7,85m
Height: 2,44m
Wing area: 15,25m²
Aspect ratio: 16,8
Empty weight: 360 kg
Max take off weight: 546 kg
Limit load factors for V_A: +5,3 –2,65
Limit load factors for V_NE: +4,0 –1,50

PERFORMANCE:

Gliding ratio:  34
Minimum rate of sink at 80 km/h: 0,75m/s
Manoeuvring speed V_A: 163km/h
Never exceed speed V_NE: 260km/h
Stall speed: 68km/h

APPROVED AEROBATIC MANOEUVRES:

   - loop
   - stall turn
   - spin
   - spiral
   - combat turn
   - fast bunt

KINDS OF OPERATIONS:

   - day flying
   - cloud flying
   - earobatics manoeuvres as above