"SWIFT" S-1
Swift is a single seat mid-wing monoplane of all-composite sfructure using
upto-date materials and manufacturing technology.
The wing, taking advantage of the successful experience gained with the
Polish KOBUZ Ill glider, is tapered with a NACA 64i412 section, without
dihedral. The load carrying wing structure is executed as a
single/double chamber torque box from the leading edge to 40% of the
chord.
The torque box is made as a monocoque sfructure of glass-fibre epoxy.
The trailing edge elements are of a sandwich sfruclure cemented to the
torque box after curing.
The airbrakes are placed off of the torque box and are operated by
push-pull rods.
The ailerons are of the Freize type, mass balanced with the articulation
axes at their lower surfaces, and are also operated by push-pull rods.
The wing tips are detachable and olher tips, giving a larger span, are
available for the non-competition person who prefers to practice more
general purpose gliding.
The fuselage is a semi-monocoque structure with reinforcing stringers in
the cockpit area and sandwich type frames in the rear. In the central
area of the fuselage are carrying frames to take the wing loads and the
landing gear suppart structure.
The tailplane is a monocoque structure with a sandwich sfructure
stabilizer.
The rudder and elevator are mass and semi-aerodynamically balanced,
controlled by cables.
The landing gear is refractable, manually operated, with a Tost brake on
the main wheel. There is a small fixed wheel on the rear fuselage.
The cockpit is ergonomically designed with an upper and lower insirument
panel, an optical system for vertical ground observation and an
instruction panel to take graphs showing the aerobatic figures to be
performed.
The upper instrument panel contains the altimeter, the airspeed
indicator, the vertical speed indicator and the compass. This panel is
opened with the canopy. The lower panel contains the accelerometer and
the knobs to open the towline catch and the air intake. There is a radio
communicalion system installed in the nose.
Technical Data :
Wing Area 11.8 m2
Wing Aspect Ratio 14.3
Wing Airfoil NACA 641412
Tail area 1.65 m2
Tail airfoil NACA 631012-63006
Vertical Empennage Area 0.9 m2
Vertical Empennage Airfoil NACA 632015-63012
Weight empty 280 kg
Weight. max in flight 390 kg
Manouver Speed VA 228 km/h
Diving Speed VD 320km/h
Max Lift/Drag Ratio at 107 km/h 30.0
Min Descent Speed at 104 km/h 0.9 m /s
Minimum Speed 73 km/h
