PZL M-17 Duduś Kudłacz
Role General aviation aircraft
Manufacturer PZL-Mielec
First flight 7 July 1977
Status prototype
Primary user Poland
Number built 1

The PZL M-17 "Duduś Kudłacz" (initially EM-5A) was a Polish twin-boom pusher general aviation and trainer aircraft of 1977, which remained a prototype.

Design and development

The aircraft was an amateur design of a team of students of Warsaw University of Technology (Politechnika Warszawska) led by Edward Margański. It had an unorthodox layout of a pusher with twin booms and very streamlined fuselage. A crew of two sat side by side, and had double controls. A tricycle landing gear was retractable.

The plane was designed in 1969-1971. At the design stage it was designated EM-5A (EM for Margański) and nicknamed Duduś Kudłacz (Hairy Duduś). The aircraft factory PZL-Mielec in Mielec got interested in the design and took over its development, under a designation PZL M-17. The design was modified there with help of Margański, plastic and duralumin construction was changed to riveted duralumin, and a less powerful engine.

The only prototype was flown on 7 July 1977 by S. Wasil. It was not produced in series. In 1979 the prototype was given to Rzeszów University of Technology. A shortcoming of a streamlined fuselage was a cramped cockpit, the crewmen were half-laying in a similar way, as in gliders.

The plane was a mid-wing monoplane. It had a two-blade wooden propeller and a 310 liter fuel tank .

Specifications

Data from Jane's all the world's aircraft, 1975-76[1]

General characteristics

  • Crew: 2
  • Length: 6.5 m (21 ft 4 in)
  • Wingspan: 9.2 m (30 ft 2 in)
  • Height: 1.7 m (5 ft 7 in)
  • Wing area: 11.3 m2 (122 sq ft)
  • Aspect ratio: 7.5
  • Airfoil: NACA 66-215
  • Empty weight: 650 kg (1,433 lb)
  • Gross weight: 900 kg (1,984 lb)
  • Max takeoff weight: 1,050 kg (2,315 lb)
  • Fuel capacity: 210 L (55 US gal; 46 imp gal)
  • Powerplant: 1 × Avia M 137 6-cyl. inverted air-cooled in-line piston engine, 130 kW (180 hp)
  • Propellers: 3-bladed controllable-pitch, 1.7 m (5 ft 7 in) diameter

Performance

  • Maximum speed: 360 km/h (220 mph, 190 kn) at sea level
  • Cruise speed: 250 km/h (160 mph, 130 kn) at 3,000 m (9,800 ft)
  • Stall speed: 95 km/h (59 mph, 51 kn) flaps down
  • Never exceed speed: 500 km/h (310 mph, 270 kn)
  • Range: 600 km (370 mi, 320 nmi)
  • Service ceiling: 6,500 m (21,300 ft)
  • Rate of climb: 7.9 m/s (1,560 ft/min)
  • Wing loading: 76.6 kg/m2 (15.7 lb/sq ft)
  • Power/mass: 0.149 kW/kg (0.091 hp/lb)

See also

Aircraft of comparable role, configuration, and era

References

  1. ↑ Taylor, John W.R., ed. (1975). Jane's all the world's aircraft, 1975-76 (66th annual ed.). New York: Franklin Watts Inc. p. 166. ISBN 978-0531032503.
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