Post WW2

Zlin Z-26 Trener / Z-126 / Z-226 / Z-326 Trener-Master / Z-526 / Z-726

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Zlin 326 Trener-Master

Designed and built in 1947, the Zlin 26 all-wood two-seat tandem trainer was superseded by the metal Zlin 126 Trener, which went into production in 1953.

Z-26 Trener prototype with pilot L.Šváb

The basic design was developed subsequently through Z 226, Z 326 Trener Master in 1957.

The Zlin 26 all-wood two-seat tandem trainer was superseded by the metal Zlin 126 Trener, which went into production in 1953.

Zlin Z-126 Trenér 2
Zlin 226 Trener
Z-326 Trener Master

Zlin built 433 Z-326s.

Zlin developed the Z 526 in 1965, and Z 726 models in both Trener (two-seat) and Akrobat (single-seat competition aircraft) variants with retractable landing gear and a variety of engines. 330 Z-526s were built.

Z-526

Production included the Z 726 trainer development of the Z-526.

As one of the world’s foremost aerobatic aircraft, the Zlin was also widely exported outside the Eastern bloc.

Gallery

Variants:

Z-26
Initial wood version

Z-126 Trener
Metal version of Z-26

Z-226A Akrobat
Fully Aerobatic version of Z-22T
Seats: 1

Z-226AS Akrobat Special
Fully Aerobatic version of Z-22T
Seats: 1

Z-226B Bohatyr
Glider towing version of Z-226T

Z-226T Trener-6
Development of Z-126

Z-326
Engine: Walter Minor 6-III, 116 hp
Wingspan: 34.777 ft / 10.6 m
Wing area: 166.304 sq.ft / 15.450 sq.m
Length: 25.656 ft / 7.82 m
Height: 6.759 ft / 2.06 m
Max take off weight: 1984.5 lb / 900.0 kg
Weight empty: 1404.6 lb / 637.0 kg
Max speed: 132 kt / 245 km/h
Cruising speed: 116 kt / 215 km/h
Initial climb rate: 866.14 ft/min / 4.4 m/s
Service ceiling: 15748 ft / 4800 m
Wing load: 11.89 lb/sq.ft / 58.0 kg/sq.m
Range: 313 nm / 580 km
Normal crew: 2
Aerobatic crew: 1

Z-326A Akrobat
Fully aerobatic version of Z-326

Z-526 Trener-Master
Development of Z-326
Pilot at rear
Prop: constant speed

Z-526A Akrobat
Fully aerobatic version of Z-526
Engine: Walter Minor 6-III K, 158 hp

Z-526AS Akrobat Special
Fully aerobatic version of Z-526

Z-526L
Engine: 1 x Lycoming AIO-360-B1B, 200 hp
Gross wt: 2175 lb
Empty wt: 1489 lb
Fuel cap: 151/262 lb
Equipped useful load: 585 lb
Payload max fuel: 323 lb
Wing loading: 12.5 lb/sq.ft
Pwr loading: 10.9 lb/hp
Range max fuel/75% pwr: 556nm/3.3hr
Service ceiling: 18,000 ft
75% cruise: 139 kt
Stall: 46-53 kt
1.3 Vso: 60 kt
ROC: 1380 fpm
Min field length: 1050 ft
Seats: 2

Z-526 AFS Akrobat
Single seat version of Z-526F
Engine: Walter Minor 6-III M-137, 130 hp
Wingspan: 29.003 ft / 8.84 m
Wing area: 148.651 sq.ft / 13.81 sq.m
Length: 25.361 ft / 7.73 m
Max take off weight: 1631.7 lb / 740.0 kg
Weight empty: 1334.0 lb / 605.0 kg
Max. speed: 132 kt / 245 km/h
Cruising speed: 116 kt / 215 km/h
Initial climb rate: 1574.8 ft/min / 8.0 m/s
Service ceiling: 16732 ft / 5100 m
Wing load: 11.07 lb/sq.ft / 54.0 kg/sq.m
Range: 421 nm / 780 km
Crew: 1

Z-526 F Trener
Engine: Avia M 137 A, 180 hp
Wingspan: 34 ft 9 in / 10.60 m
Wingspan over tip tanks: 35 ft 11.5 in / 10.96 m
Length: 26 ft 3 in / 8.00 m
Empty weight: 1465 lb / 665 kg
MTOW Aerobatic: 2072 lb / 940 kg
MTOW normal: 2150 lb / 975 kg
Max cruise max norm TOW: 113 kt / 130 mph / 210 kph
ROC SL max norm TOW: 1181 fpm / 360 m/min
Service ceiling max norm TOW: 17,060 ft / 5200 m
Max range std fuel max norm TOW: 255 nm / 295 mi / 480 km
Max range w/tiptanks max norm TOW: 450 nm / 520 mi / 840 km
Seats: 2 tandem
Glider tow option

Z-726 Universal
Similar to Z-526F, shorter wing span
Engine: M 137 AZ, 180 hp

Zlin 526 AFS

Zlin Z-25 Sohaj / Ottokowice Max Prip Z-25/4

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Z-25/4

Glider, Czech Republic, 1945

Designed by Ladislav Smrecek and also manufactured by Ottokowice Max Prip.

Length : 23.458 ft / 7.15 m
Wingspan : 49.213 ft / 15.0 m
Wing area : 150.696 sq.ft / 14.00 sq.m
Max take off weight : 599.8 lb / 272.0 kg
Weight empty : 401.3 lb / 182.0 kg
Max. speed : 116 kt / 215 km/h
Landing speed : 27 kt / 50 km/h
Wing load : 3.90 lb/sq.ft / 19.00 kg/sq.m
Glide ratio : 27.0
Seats: 1

Max Prip, Ottokowice Zlin 25/4
Wing span: 15 m
Wing area: 14 sq.m
Aspect ratio: 16.1
Empty Weight: 185 kg
Gross Weight: 265 kg
Wing Load: 18.9 kg/sq.m
MinSink: 0.65 m/s 60 kph
L/DMax: 27 75 kph
Seats: 1

Zlin Z-24 Krajanek

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The 1945 Zlinn Z-24 Krajanek was the first Czechoslovak aircraft post war.

Length : 20.636 ft / 6.29 m
Wingspan : 39.764 ft / 12.12 m
Wing area : 145.314 sq.ft / 13.5 sq.m
Max take off weight : 496.1 lb / 225.0 kg
Weight empty : 297.7 lb / 135.0 kg
Max. speed : 108 kts / 200 kph
Landing speed : 25 kts / 46 kph
Wing load : 3.49 lb/sq.ft / 17.0 kg/sq.m
Glide ratio : 18.0
Crew : 1

Zlin Z-23 Honza

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Glider, Czech Republic, 1950

Length : 20.899 ft / 6.37 m
Wing span : 32.808 ft / 10.0 m
Aspect ratio: 7.0
Wing area : 157.154 sq.ft / 14.6 sq.m
Max take off weight : 396.9 lb / 180.0 kg
Weight empty : 209.5 lb / 95.0 kg
Max. weight carried : 187.4 lb / 85.0 kg
Max. speed : 49 kts / 90 kph
Landing speed : 23 kts / 42 kph
Wing load : 2.46 lb/sq.ft / 12.0 kg/sq.m
Glide ratio : 10.0
Crew : 1

Zlin Z-22 Junak / Z-122

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Zlin 22

The Zlin 22 appeared in 1947 as a two-seat trainer, powered by a Zlin Persy III engine of 57 hp.

When production of the Persy engine was discontinued, the Zlin 22 was re-engined with a 75 hp Praga D as the Zlin 22D, and a 105 hp Walter Minor 4-III as the three seat Zlin 22M.

Two prototypes of the Zlin 122 version were produced. Three/four seat, they were powered by a 105 hp Zlin Toma 4 engine.

Zlin 22
Engine: Zlin Persy III, 57 hp
Wingspan: 34 ft 9 in
Length: 23 ft 9 in
Height: 6 ft 5 in
Wing area: 157.7 sq,ft
Seats: 2

Zlin 22D
Engine: Praga D, 75 hp
Wingspan: 34 ft 9 in / 10.6 m
Length: 23 ft 9 in / 7.25 m
Height: 6 ft 5 in
Wing area: 157.7 sq,ft / 14.6 sq.m
Empty weight: 804 lb / 365.0 kg
Loaded weight: 1399 lb
Wing load: 8.2 lb/sq.ft / 40.0 kg/sq.m
Max speed: 112 mph / 95 kts / 176 km/h
Cruise: 100 mph / 84 kts / 155 km/h
Service ceiling: 13,780 ft / 4200 m
Range: 435 mi / 270 nm / 500 km
Seats: 2

Zlin 22M
Engine: Walter Minor 4-III, 105 hp
Wingspan: 34 ft 9 in
Length: 23 ft 9 in
Height: 6 ft 5 in
Wing area: 157.7 sq,ft
Empty weight: 926 lb
Loaded weight: 1588 lb
Max speed: 133.5 mph
Cruise: 121 mph
Ceiling: 18,040 ft
Range: 620 mi
Seats: 3

Zlin 122
Engine: Zlin Toma 4, 105 hp
Seats: 3-4

Zlin Z 22 Junak

Zenair Zipper

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Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading edge, swept for¬ward trailing edge and tapering chord; con¬ventional tail. Pitch control by fully flying tail; yaw control by fully flying rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile double surface. Undercarriage has three wheels in tricycle formation; glass fibre sus¬pension. Push right go right nosewheel steer¬ing connected to yaw control. Aluminium tube and sheet framework, with optional total enclosure pod. Engine mounted at wing height driving tractor propeller. All aluminium and hardware is of aircraft quality.
The Zipper is a conventional three axis machine with rudder pedals and centre stick, and it appears to be quite conventional in its choice of materials, being basically a tube and Dacron machine. There are some interesting features though, such as the tail boom, which is not tubular but is constructed of sheet aluminium alloy formed into a rectangular cross section.
Most of the innovation, however, is centred on the wing design, which has an unusual shape plan, with ailerons attached to the trailing edges. The design allows the wing to be folded in two minutes, the maker claims, after which the aircraft can be towed on its own wheels, avoiding the expense of a trailer.
Engine is the direct drive JPX PUL425, which is available in two states of tune 22 hp standard or 26hp with tuned exhaust. The aircraft is sold in kit form, but Zenair says the kit takes only an afternoon to complete, having already been test assembled in the factory before shipping. Other options include floats and wheel spats, while an enclosed cockpit, skis and propeller spinner are also offered.

Length overall 14.5 ft, 4.42 m
Height overall 5.5ft, 1.68m
Wing span 28.0ft, 8.53m
Mean chord 5.0ft, 1.52m
Sweepback 0 deg
Total wing area 140 sq.ft, 13.0 sq.m
Wing aspect ratio 5.6/1
Engine: JPX PUL425, 22hp at 4600rpm
Propeller diameter 42 inch, 1.07 m
No reduction
Max static thrust 180 lb, 82 kg
Power per unit area 0.16hp/sq.ft, 1.7hp/sq.m
Fuel capacity 6.0 US gal, 5.0 Imp gal, 22.7 litre
Empty weight 180lb, 82kg
Max take off weight 420 lb, 191 kg
Payload 240 lb, 109 kg
Max wing loading 3.00 lb/sq.ft, 14.7 kg/sq.m
Max power loading 19.1lb/hp, 8.7kg/hp
Load factors +6.0, 3.0 design
Max level speed 50 mph, 80 kph
Never exceed speed 80 mph, 129 kph
Cruising speed 40mph, 64 kph
Stalling speed 20 mph, 32 kph
Max climb rate at sea level 700 ft/min, 3.6 m/s
Take off distance 120 ft, 35 m
Landing distance 80 ft, 25 m
Range at average cruising speed 100 mile, 161 km
Seats: 1