Top speed 133 km/h First flight May 20, 1927 | Length 6.93 m | |
Manufacturer Podlaska Wytwórnia Samolotów | ||
The PWS-3 was a Polish sports aircraft, developed in 1927 by PWS (Podlaska Wytwórnia Samolotów - Podlasie Aircraft Factory), which remained a prototype.
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Design and development
The PWS-3 was the first sports aircraft manufactured by the Polish aerospace industry (not counting earlier amateur designs). It was designed by Stanisław Cywiński in the PWS factory in 1927. Its interesting feature was a fuselage built upon a bottom boom, what made possible changing of upper fuselage part with cockpits, and developing single-seater, two-seater or other specialized variants.
The prototype of the PWS-3, designated PWS-3B, was flown on 20 May 1927 at Biała Podlaska. After trials, a rudder got improved. In 1928 the plane underwent a modification, receiving rounded wingtips instead of square ones, and smaller ailerons.
Operational history
The prototype PWS-3B was given a registration number P-PWSS, from 1930: SP-ACJ. It took part in the 1st Polish Light Aircraft Contest on 6–9 October 1927, taking the 2nd place (after JD-2 aircraft). Later it was bought by the LOPP paramilitary organization in Lublin and used for propaganda flights.
Construction
The PWS-3 was a two-seater parasol wing braced monoplane of wooden construction. The fuselage was built around a box-section wooden boom, with a kind of superstructure of wood strips, covered with plywood in front and aircraft fabric fairing in the rear. The engine compartment was covered with duralumin sheeting. The empennage was wooden, with the fixed surfaces plywood covered and fabric on the control surfaces. The rectangular wooden wings had two spars, and were covered with plywood in front and fabric in the rear. Initially it had slotted ailerons on all span, later shortened. The fuselage had two cockpits in tandem, with windscreens and dual controls. The undercarriage consisted of a fixed split axle conventional landing gear, with a rear skid. Both main undercarriage struts and wing struts were fixed to small horizontal winglets at the bottom of fuselage sides. Fuel was carried in two tanks, 100 l capacity in total, in a central wing section.
The 5-cylinder Walter NZ 60 air-cooled radial engine was giving a nominal power of 60 hp and take-off power of 65 hp, driving a two-blade fixed pitch wooden propeller. A cruise fuel consumption was 22 l/h.
Specification (PWS-3B)
Data from Glass, A. (1977), p.179
General characteristics
Performance