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PZL-102 Kos
|
|
Role
|
Two-seat touring/training monoplane
Type of aircraft
|
Manufacturer
|
PZL
|
First flight
|
23 May 1958
|
Introduction
|
1959
|
Produced
|
1959-1962
|
Number built
|
10
|
The
PZL-102 Kos
(
blackbird
) is a Polish two-seat touring and training monoplane designed and built by
PZL
.
Development
[
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]
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. 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 65 hp (48 kW)
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
[
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]
Between 13 May and 8 June 1960 Antoni Szyma?ski 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
[
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]
- 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
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]
Specifications (PZL-102B)
[
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]
Data from
Jane's All the World's Aircraft 1962-63,
[1]
The Illustrated Encyclopedia of Aircraft
[2]
General characteristics
- Crew:
2
- Length:
6.97 m (22 ft 10 in)
- Wingspan:
8.49 m (27 ft 10 in)
- Height:
1.88 m (6 ft 2 in)
- Wing area:
11.02 m
2
(118.6 sq ft)
- Airfoil
:
NACA 43012A
[3]
- Empty weight:
418 kg (922 lb)
- Max takeoff weight:
630 kg (1,389 lb)
- Fuel capacity:
75 L (19.8 US gal; 16.5 imp gal)
- Powerplant:
1 ×
Continental C90-12F
4-cylinder air-cooled horizontally-opposed piston engine, 71 kW (95 hp)
- Propellers:
2-bladed fixed-pitch wooden propeller, 1.8 m (5 ft 11 in) diameter
Performance
- Maximum speed:
193 km/h (120 mph, 104 kn)
- Cruise speed:
174 km/h (108 mph, 94 kn)
- Stall speed:
69 km/h (43 mph, 37 kn) with flaps down
- Never exceed speed
:
300 km/h (190 mph, 160 kn)
- Range:
640 km (400 mi, 350 nmi) at 135 km/h (84 mph; 73 kn)
- Service ceiling:
3,800 m (12,500 ft)
- Rate of climb:
3.5 m/s (690 ft/min)
- Wing loading:
57.2 kg/m
2
(11.7 lb/sq ft)
- Power/mass
:
0.1126 kW/kg (0.0685 hp/lb)
- Take-off run:
460 m (1,510 ft)
- Take-off distance to 15 m (49 ft):
1,300 m (4,300 ft)
- Landing distance from 15 m (49 ft):
1,100 m (3,600 ft)
References
[
edit
]
- ^
Taylor, John W.R., ed. (1962).
Jane's All the World's Aircraft 1962-63
. London: Sampson Low, Marston & Co.
- ^
The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985)
. Orbis Publishing. p. 2675.
- ^
Lednicer, David.
"The Incomplete Guide to Airfoil Usage"
.
m-selig.ae.illinois.edu
. Retrieved
16 April
2019
.
Further reading
[
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]
- Taylor, Michael J. H. (1989).
Jane's Encyclopedia of Aviation
. London: Studio Editions.
External links
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]