PZL.26

The PZL.26 was a development of the PZL.19, that was built for previous Challenge 1932 contest. Like its predecessor, it was designed by Jerzy Dąbrowski and Franciszek Misztal in 1933. The plane was an all-metal cantilever low-wing monoplane with a fixed landing gear and a closed canopy. It retained wings and tail of the PZL.19, with minor changes. A fuselage, wings and landing gear were more streamlined and strengthened. The main change was a stronger engine, a US-made 265 hp Menasco Buccaneer B-6S3 engine. The engine choice appeared to be a failure, though. Five aircraft were built in 1934 and one prototype for static trials. They carried registration markings: SP-PZL to PZP. ==Operational history==

All five PZL.26s took part in the Challenge from August 28 to September 16, 1934. A 9538 km long rally over Europe appeared too difficult for engines, and three aircraft failed to finish the rally due to engine breakdowns (pilots: Szczepan Grzeszczyk, Andrzej Włodarkiewicz and Jan Balcer). Piotr Dudziński (SP-PZL) took the 11th place and Ignacy Giedgowd (SP-PZM) the 17th place (by coincidence, these results were similar to those of PZL.19s, two years earlier). Giedgowd's engine failed during a maximum speed trial, though. It is noteworthy, that they had the 2nd and 4th results of average speed in the rally - 211 and 213 km/h. In Autumn 1934, the PZL.26 SP-PZM was presented at the Paris Air Show. Because of unreliable engines and quite big fuel consumption resulting from their high power output, most PZL.26s were not used in Polish sports aviation much after the Challenge. SP-PZL, -PZM, -PZN and - PZP were removed from the registry on July 1, 1936. The SP-PZO was used until the war in 1939 by the Pomeranian Aeroclub in Toruń. Possibly also the other one was used in this Aeroclub. In 1939 Jerzy Dąbrowski made a preliminary design of a fast fighter plane PZL.55, being a far development of the PZL.26's construction, powered by Hispano-Suiza 1100 hp engine, but it was not realized due to World War II. ==Description==

Metal construction low-wing monoplane, conventional in layout. Fuselage of a steel frame covered with duralumin in front and canvas in the rear. Trapezoid three-part wing with elliptical ends, covered with duralumin. Wings were fitted with automatic slats and split flaps. Wings were folding rearwards. Cab had three seats in tandem, under a common multi-part canopy, with double controls for the first two crewmen. Fixed landing gear with a rear skid, main wheels in massive aerodynamical covers. Two-blade metal propeller. Fuel tanks in wings and smaller one in the fuselage (180 L). Cruise fuel consumption 60 L/h. ==Specifications==