Zlín Z 526

The Zlin Z-526 Akrobat is a Czech sports plane used in aerobatics.

Zlin Z-526
Role Sports plane
Manufacturer Zlin Aircraft
First flight 1959
Number built 1,400+

History

The Z-526 was originally designed by Zlin Aircraft in 1959. Its two-seat version is called the Trener-Master

The Z 526's layout was organized with the pilot in the rear, and the student in front. The aircraft could be equipped also with tip tanks and a constant speed propeller. The Z-526F was introduced in 1968 and was equipped with a 135 kW (180 hp) Avia M 137A engine, the export version Z-526L differing by being equipped with a 150 kW (200 hp) Lycoming AEIO-360 flat-four. Single-seat versions included the Z-526A, Z-526AS, and the Z-526AFS.

The Z-526 AFM was built between 1981 and 1984 and was powered by a 155 kW (210 hp) Avia M337 engine, had tip tanks and a lengthened fuselage. The aircraft was later developed into the Zlin Z-726.

More than 1,400 Z-526s were manufactured, many for military and private flying schools.

Variants
Z-526
Two-seat version
Z-526A
Single-seat version
Z-526AF
Single-seat version
Z-526AFS
Single-seat version
Z-526AFM Condor
powered by an Avia M337 inverted six-cylinder engine giving 210hp(157kW)

Aircraft On Display
Serbia

A Zlin Z-526M is on display.

Specifications (Z-526 Trener-Master)

Data from Jane's all the World's Aircraft 1968–69[1]

General characteristics

  • Crew: 2 (526A / 526F - 1)
  • Length: 7.8 m (25 ft 7 in)
  • Wingspan: 10.6 m (34 ft 9 in)
  • Height: 2.06 m (6 ft 9 in)
  • Wing area: 15.45 m2 (166.3 sq ft)
  • Airfoil: root: NACA 2418; tip: NACA 4412[2]
  • Empty weight: 680 kg (1,499 lb)
Z 526A 650 kg (1,430 lb)
  • Max takeoff weight: 975 kg (2,150 lb) (trainer)
940 kg (2,070 lb) (aerobatic)
Z 526A 830 kg (1,830 lb) (aerobatic)
  • Fuel capacity: 2x 45 l (12 US gal; 9.9 imp gal) tanks in the wing roots, with a 7 l (1.8 US gal; 1.5 imp gal) gravity collector tank in the fuselage.
  • Powerplant: 1 × Walter Minor 6-III 6-cylinder air-cooled inverted in-line piston engine, 120 kW (160 hp) (later variants 155 kW (208 hp) Avia M337)
  • Propellers: 2-bladed V 503, 1.9 m (6 ft 3 in) diameter constant-speed propeller

Performance

  • Maximum speed: 220 km/h (140 mph, 120 kn) at sea level
  • Cruise speed: 208 km/h (129 mph, 112 kn) (70% power)
  • Landing speed: 78 km/h (48 mph; 42 kn)
  • Never exceed speed: 320 km/h (200 mph, 170 kn)
  • Range: 580 km (360 mi, 310 nmi)
  • Ferry range: 610 km (380 mi, 330 nmi) with wing-tip tanks
  • Service ceiling: 5,000 m (16,000 ft)
  • Rate of climb: 5 m/s (980 ft/min) at sea level
  • Take-off run: 220 m (720 ft)
  • Landing run: 135 m (443 ft)

References
  1. Taylor, John W.R., ed. (1968). Jane's all the World's Aircraft 1968–69. London: Sampson Low, Marston & Company. p. 26.
  2. Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.