Z 50 LS Aircraft/Reading/EN

Z-50 LS aircraft manufacturer: Moravan Otrokovice. The special aerobatic aircraft Zlin Z-50 LS was developed for demanding customers wishing to participate with this aircraft in top aerobatic contests. The Z-50 LS aircart performance permits to fly all figures met in top aerobatic events. The aircraft is a single engine single seat cantilever low wing monoplane with closed cockpit and fixed undercarriage.
The symmetric wing profile improves flying characteristics during inverted flying. A suitable configurations of the wing and tailplanes, the shape of tailplanes and their mutual configuration result in excellent properties during the main aircraft task - maximum aircraft controllability during aerobatics - as well as in excellent flying characteristics of the aircraft during normal flying. Ailerons over the entire wing span result in a high roll speed even at low flying speeds.
Main specifications:
wing span withou wingtip tanks 8.850m
wing span with wingtip tanks 9.030m
length 6.620m
height on ground 1.985m
wing area 12.500m2
aileron area (2 x 1.4m2) 2.800m
take off rung to 15m altitude 300m
landing distance from 15m altitude 580m
maximum airspeed (CAS) 337km/h
maximum level airspeed (TAS) 308km/h
cruising speed (TAS) 275km/h
load multiples +8 -6g
+3.8 -1.5g
Power plant: LYCOMING AEIO-540 L 1B50 boxer piston engine, four stroke, six cylinders, air cooled rated at 220kW (300hp) modified for aerobatics. This is a modern engine with fuel injection, with a special lubricating system and with a favourable power to weigth ratio.
HOFFMANN HO.V 123 K-V 200 AH three bladed propeller, with hydraulically controlled blade pitch and with constant speed. The fuselage is an all metal semi-monocoque structure. A firewall separates the engine compartment from the cockpit. The firewall carries engine bed hinges and hinges for removable engine hoods. A semi-intergrated fuel tank is installed behind the firewall.
The trapezoid wing is an all metal cantilever structure with throughgoing main spar. The wing is anchored to the fuselage by bolts. Ailerons are mass balanced all metal structures. Ailerons carry automatic flettners and loading tabs which influence force in roll control elements. A fixed trim tab permits basic trimming. The wing does not carry any lift flaps. Wing tips are designed to permit attachment of wing tip tanks.
Tailplanes of mixed design have a metal carcass with partially metal and partially canvas skin. The stabilizer is supported by a pair of externally mounted struts. The fin is permanently atteched to the fuselage. The elevator carries a controllable trim tab and an automatic flettner. The rudder carries an automatic flettner.
Landing gear consists of the main undercarriage and of a tail undercarriage. The main unercarriage is attached to the fuselage on its bottom side just in front of the main spar. A flat titanium leaf spring serves as undercarriage legs. Wheels carry mechanical brakes controlled by pedals attached to foot controls. The tail undercarriage consits of an axially mounted flat spring and a tailwheel. The tailwheel can be locked in its center position to maintain a straight direction during take off and landing.
The cockpit is equipped with flight instruments and engine monitoring instruments as well as with necessary flight controls. An adjustable seat and ajustable pedals permit each pilot to select an optimal seating position. The seat backrest is shaped to permit to fly with a backpack parachute. Five point seat belts attach firmly each pilot to the seat.
The cockpit canopy is an integral structure without a separate windshield. The canopy opens to the side and it is jettisonable in flight. The cokpit provides good overall view and adequate comfort in flight. It is equipped with an adjustable ventillating flap.
The main fuel tank capacity is 60 litres, that of wingtip tanks is 2 x 50 litres. The fuel and lubricating systems are laid out for full aerobatic flying including inverted flying.