PZL-105 Flaming
PZL-105 at the Polish Aviation Museum
Role Utility aircraft
Manufacturer PZL Warszawa-Okęcie
First flight 9 November 1989
Status Prototype
Primary user Polish civilian aviation
Number built 2 (prototypes)

The PZL-105 Flaming (flamingo) is a Polish short-takeoff-and-landing (STOL) utility aircraft designed by PZL "Warszawa-Okęcie". It remained a prototype.

Development

The PZL-105 was designed as a successor to the successful utility aircraft PZL-104 Wilga, being more modern and economical and offering increased transport capacity. The design was initially called Wilga 88. It retained the high-wing layout of the PZL-104 and the upward-opening side doors, but it was a completely new aircraft. Compared with the Wilga, it has a six-seat cabin instead of four seats and the wings are supported by single struts instead of a cantilever design. The plane was intended for a variety of purposes, like glider towing, parachute training, transport, air ambulance, patrolling and crop dusting (with 500 kg of chemicals). Also, a seaplane variant was intended.

The first prototype, powered by a 265 kW (360 hp) Russian M-14P radial engine, was first flown on 9 November 1989 (markings SP-PRC). An intended designation of a serial variant was PZL-105M. The second prototype, designated PZL-105L, was fitted with a flat engine 298 kW (400 hp) Lycoming IO-720. It was flown on 27 July 1991 (markings SP-PRD). There was also made one prototype for static trials.

Problems with funding at the outbreak of the 1980s and 1990s, connected with a change of political system in Poland, and the priority of the PZL-130 Orlik trainer program, had caused the Flaming program to be suspended, and production of the type has yet to have started. The company developed a new variant of the PZL-104, the Wilga 2000 with Lycoming I0-540 flat engine instead.

Design

Metal construction braced high-wing monoplane, conventional in layout, duralumin covered. Semi-monocoque fuselage. Rectangular single-spar wings, fitted with Fowler flaps and slotted flaperons. Six-seat cabin with three rows of seats, with large side doors opening upwards. Conventional fixed landing gear with tail wheel, the main gear is made of composite spring legs. Two-blade or three-blade (PZL-105L) metal propeller. Fuel tanks in wings (270 L).

Surviving aircraft

The first prototype and the second prototype airframe (lacking engine) are in a collection of the Polish Aviation Museum in Kraków.

Specifications (PZL-105M)

Data from Jane's All The World's Aircraft 1993-94.[1]

General characteristics

  • Crew: 1
  • Capacity: 5 pax / 450 kg (990 lb) cargo
  • Length: 8.7 m (28 ft 7 in)
PZL-105L 8.67 m (28.4 ft)
  • Wingspan: 12.97 m (42 ft 7 in)
  • Height: 2.87 m (9 ft 5 in)
  • Wing area: 16.9 m2 (182 sq ft)
  • Aspect ratio: 9.95
  • Airfoil: NASA GA(W)-1
  • Empty weight: 1,130 kg (2,491 lb)
PZL-105L 1,150 kg (2,540 lb)
  • Max takeoff weight: 1,850 kg (4,079 lb)
  • Fuel capacity: 270 L (71 US gal; 59 imp gal) in two integral wing tanks
  • Powerplant: 1 × Vedeneyev M-14P 9-cylinder air-cooled radial piston engine, 268.5 kW (360.1 hp)
PZL-105L 298 kW (400 hp) Lycoming IO-720-A1B
  • Propellers: 2-bladed W-530TA-D35, 2.4 m (7 ft 10 in) diameter constant-speed propeller
PZL-105L 3-bladed 2.18 m (7 ft 2 in) diameter Hartzell constant-speed propeller

Performance

  • Maximum speed: 245 km/h (152 mph, 132 kn)
PZL-105L 260 km/h (160 mph; 140 kn)
  • Cruise speed: 205 km/h (127 mph, 111 kn) max
188 km/h (117 mph; 102 kn) economical
PZL-105L 235 km/h (146 mph; 127 kn) max
PZL-105L 216 km/h (134 mph; 117 kn) economical
  • Stall speed: 102 km/h (63 mph, 55 kn) flaps down engine idling
  • Never exceed speed: 306 km/h (190 mph, 165 kn)
  • Range: 1,044 km (649 mi, 564 nmi) at max cruising speed
1,085 km (674 mi; 586 nmi) at economical cruise speed
PZL-105L 853 km (530 mi; 461 nmi) at max cruising speed
PZL-105L 981 km (610 mi; 530 nmi) at economical cruise speed
  • Service ceiling: 4,140 m (13,580 ft)
PZL-105L 5,070 m (16,630 ft)
  • g limits: +3.8 -1.52
  • Rate of climb: 5.5 m/s (1,080 ft/min) at sea level
PZL-105L 5.6 m/s (1,100 ft/min)
  • Wing loading: 109.5 kg/m2 (22.4 lb/sq ft)
  • Power/mass: 0.145 kW/kg (0.088 hp/lb)
PZL-105L 0.161 kW/kg (0.098 hp/lb)
  • Take-off: 176 m (577 ft)
  • Landing: 153 m (502 ft)
  • Take-off to 50 m (160 ft): 338 m (1,109 ft)
  • Landing from 50 m (160 ft): 326 m (1,070 ft)
PZL-105L
  • Take-off: 189 m (620 ft)
  • Landing: 157 m (515 ft)
  • Take-off to 50 m (160 ft): 351 m (1,152 ft)
  • Landing from 50 m (160 ft): 330 m (1,080 ft)

See also

Related development

References

  1. ↑ Lambert, Mark; Munson, Kenneth; Taylor, Michael J.H., eds. (1993). Jane's all the world's aircraft, 1993-94 (84th ed.). London: Jane's Information Group. pp. 241–242. ISBN 0710610661.

Further reading

  • Taylor, John W.R.; Munson, Kenneth; Taylor, Michael J.H., eds. (1989). Jane's all the world's aircraft, 1989-90 (Eightieth birthday ed.). London: Jane's Information Group. pp. 203–204. ISBN 0710608969.
  • Glass, Andrzej (1994). Samoloty '94. Warsaw: Grupa IMAGE. ISBN 83-85461-19-1.
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