|Primary user||Polish Air Force|
Design and development
The PWS-6 was a successor of an earlier liaison aircraft design, the PWS-5, which was not accepted for mass production. The designers, Aleksander Grzędzielewski and Augustyn Bobek-Zdaniewski, utilized the experience they had gained on PWS-11 and PWS-12 trainers, and as a result the new plane had improved aerodynamics, an oval shaped fuselage section and rounded wingtips. The layout of wings and their bracing were similar to the PWS-5, as was the engine and fixed undercarriage, while the front of the fuselage and the empennage was similar to a final variant of the PWS-12. It was the first Polish aircraft fitted with slats.
The design was produced in 1929–1930 and a scale-model of the aircraft was tested in the wind-tunnel. The prototype was built on the factory's own initiative and first flew in late 1930 in Biała Podlaska, piloted by Franciszek Rutkowski. In 1931 it was tested in the Aviation Technical Research Institute (ITBL) in Warsaw. It was evaluated as much better than the PWS-5, with better performance, good handling and a short landing. However, the aircraft was not produced, because the Polish Air Force had just ordered a production of the Lublin R-XIII aircraft.
The PWS-6 was a two-seater biplane of a wooden construction. A fuselage, oval in cross-section, was covered with canvas skin on a wooden frame, except the engine part, which was covered with aluminium sheets. The wings were two-spar, two-section, rectangular with rounded tips, covered with canvas and plywood (in front). Lower and upper wings halves had the same dimensions, therefore the upper wing had smaller span, lacking a central section. The upper wing was staggered forward, and connected with a lower wing by N-shaped struts and a slanted transverse strut, without wires. The empennage was of wooden construction, canvas covered.
The two-man crew sat in tandem in open cockpits. The rear observer's cockpit could be fitted with a ring machine gun mounting in case of serial production. The plane had a fixed, split axle conventional landing gear, with a rear skid. The fuel tank was located in the fuselage, in front of the cab. It had a maximum capacity of 210 L, but the normal capacity was 190 L.
The engine was a 9 cylinder Skoda-Wright Whirlwind J-5 air-cooled radial engine, built under licence in the Polish Skoda Works. Its nominal power was 220 hp, the take-off power was 240 hp. The engine had a Townend ring. The propeller was a wooden Szomański two-blade with a fixed pitch, although later a metal Ratier propeller with an adjustable-pitch was also tried. Cruise fuel consumption was 45–50 L/h.
Data from Glass, A. (1977), p.183
- Crew: 2
- Length: 6.98 m (22.9 ft)
- Wingspan: 9.6 m (31 ft)
- Height: 2.95 m (9.7 ft)
- Wing area: 25.00 m² (270 sq ft)
- Empty weight: 800 kg (1,800 lb)
- Loaded weight: 1175 kg (2,590 lb)
- Useful load: 375 kg (830 lb)
- Powerplant: 1 × Skoda-Wright Whirlwind J-5 air-cooled 9-cylinder radial 2 blade fixed pitch, 220 hp (164 kW)
- Maximum speed: 186 km/h (116 mi/h)
- Cruise speed: 160 km/h (99 mi/h)
- Stall speed: 70 km/h (43 mi/h)
- Range: 640 km (400 mi)
- Service ceiling: 4,530 m (14,860 ft)
- Rate of climb: 5.85 m/s (19.2 ft/s)
- Wing loading: 47 kg/m² (10 lbs/ft²)
1 machine-gun (planned)
- Related development
- Aircraft of comparable role, configuration and era
- Glass (1977), pp. 182–183.
- Cynk (1971).
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