PZL-102 Kos

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PZL-102 Kos
PZL102 Kos.jpg
Role Two-seat touring/training monoplane
Manufacturer PZL
First flight 23 May 1958
Introduction 1959
Produced 1959-1962
Number built 10

The PZL-102 Kos is a Polish two-seat touring and training monoplane designed and built by PZL.

Development[edit]

First flown on 21 May 1958 by Mieczysław Miłosz the PZL-102 was designed as a semi-aerobatic two-seat light monoplane and was later given the name Kos (Blackbird). The Kos was an all-metal low-wing cantilever monoplane with fabric tail control surfaces. It had a fixed tailwheel landing gear and the prototype had a nose-mounted 65hp (48kW) Narkiewicz WN-1 flat-four engine. The Kos had an enclosed cockpit for two side-by-side. After a number of prototypes the production aircraft (designated PZL-102B) first flew in October 1959, with Continental C90 engine and changed wing construction. Only short series was produced, because it needed imported engine.

Operational history[edit]

Between 13 May and 8 June 1960 Antoni Szymański made 9000 km commercial flight on PZL-102B on route Warsaw - Vienna - Geneva - Reims - London - Luxembourg - Berlin - Warsaw.

Seven aircraft were sold abroad. Austrian aircraft were operated for agrospraying purposes. Tank filled with chemical agent was placed on the passenger seat.

One PZL-102 has been restored to airworthy condition (markings SP-EFA).

PZL 102B restored on Brazil, currently on sale.

Variants[edit]

PZL-102A
Prototypes
PZL-102B
Production variant with Continental C90 engine.

There is another PZL 102B restored in South Africa, based at Jack Taylor Airfield Krugersdorp, and one more in Brazil (PT-BGP)

Operators[edit]

Specifications (PZL-102B)[edit]

Data from The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. p. 2675. 

General characteristics

  • Crew: 1 pilot
  • Capacity: 1 passenger
  • Length: 6.95 m (22 ft 9½ in)
  • Wingspan: 8.50 m (27 ft 10½ in)
  • Height: 1.90 m (6 ft 2¾ in)
  • Wing area: 11 m2 (118.41 ft2)
  • Empty weight: 418 kg (992 lb)
  • Gross weight: 655 kg (1444 lb)
  • Powerplant: 1 × Continental C90-12F flat-four piston engine, 71 kW (95 hp)

Performance

  • Maximum speed: 190 km/h (118 mph)
  • Range: 640 km (398 miles)
  • Service ceiling: 4600 m (15,090 ft)

References[edit]

  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions. 
  • The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. p. 2675. 

External links[edit]