PZL-102
| PZL-102 Kos | |
|---|---|
|
|
| Type: | Sports , school and travel aircraft |
| Design country: | |
| Manufacturer: | |
| First flight: |
May 23, 1958 |
| Production time: |
1958-1964 |
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The PZL-102 Kos (Blackbird) is a sport , school and touring aircraft developed towards the end of the 1950s in the branch of the Polish state aviation industry in Warszawa-Okęcie .
development
The design work was carried out under the direction of Stanisław Lassota and began in 1957. The first prototype was completed in May 1958 and made its maiden flight on the 23rd of the month. It was powered by a local WN-1 engine with 65 hp, which turned out to be too weak. The few series copies built from October 1959 and designated as P-102B were therefore equipped with a US 90 hp engine from Continental . Production stopped in 1964. The PZL-102 was approved for simple aerobatics .
construction
The PZL-102 is a self - supporting low- wing aircraft . The front part of the fuselage consists of a sheet-metal-clad and welded tubular steel frame up to the end of the cockpit , the rear part is formed from half-shells and connected to the front part with four bolts. The cabin with two seats next to each other has dual controls, with the right controls including the rudder pedals being removed if necessary. Behind it there is a storage space for luggage and underneath the 60 l fuel tank. The pilot's cabin is covered by a plexiglass full-view hood that can be pushed back and can be thrown off in an emergency.
The wing, which consists of a metal frame, is made in two parts and has a single spar and is equipped with expanding flaps up to the middle of the fuselage and differential ailerons . The front edge has light metal planking, the rest is covered with fabric. The cantilevered normal tail unit is a fabric-covered metal frame with aerodynamic and mass-balanced rudders. The area for the elevator and vertical stabilizer is 1.94 m² and 0.9 m², respectively.
The PZL-102 is equipped with a non-retractable rear wheel landing gear, the main wheels of which (400 × 150 mm) have a track width of 1780 mm and are equipped with oil-air suspension and hydraulic brakes coupled with the rudder. The star wheel with the dimensions 200 × 80 mm has rubber suspension and can be swiveled in all directions.
Technical specifications
| Parameter | Data (prototype) | Data (PZL-102B) |
|---|---|---|
| crew | 2 | |
| span | 8.49 m | |
| length | 6.38 m | |
| height | 1.88 m | |
| Wing area | 11.02 m² | |
| Wing loading | 52 kg / m² | 57 kg / m² |
| Preparation mass | 383 kg | 403 kg |
| Payload | 207 kg | 227 kg |
| Takeoff mass | 590 kg | 630 kg |
| drive | an air-cooled four - cylinder boxer engine with a rigid two-bladed wooden propeller M 63 / M 30 (ø 1.7 m) |
|
| Type | Narkiewicz WN-1 | Continental C90-12F |
| Starting power rated power |
70 hp (51 kW) 65 hp (48 kW) |
95 PS (70 kW) 90 PS (66 kW) |
| Fuel volume | 60 l | |
| Fuel consumption | 11 l / h | |
| Top speed | 170 km / h | 198 km / h |
| Cruising speed | 150 km / h | 175 km / h |
| Max. permissible speed | 260 km / h | 300 km / h |
| Minimum speed | 82 km / h without flaps 75 km / h with flaps |
93 km / h without flaps 80 km / h with flaps |
| Rate of climb | 2.3 m / s near the ground | 4.1 m / s near the ground |
| Rise time | 8.5 min at 1000 m altitude 41.0 min at summit height |
4.5 min at 1000 m altitude 47.5 min at the summit |
| Service ceiling | 2700 m | 4600 m |
| Range | 450 km | 625 km |
| Flight duration | 4 h | |
| Take-off run | 235 m | 110 m |
| Take-off line at 15 m height | 600 m | 380 m |
| Landing distance from a height of 15 m | 325 m | |
| Coasting distance | 235 m | 175 m |
literature
- PZL-102 Kos. In: Aerosport. 5/1960, Sport und Technik, Berlin, pp. 17-20.
- Peter Alles-Fernandez (Ed.): Aircraft from A to Z. Volume 3. Bernard & Graefe, Koblenz 1989, ISBN 3-7637-5906-9 , p. 200.
