PZL-105 Flaming
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 IO-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 / Template:Cvt cargoTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/lengthTemplate:Aircraft specs/convertTemplate:Aircraft specs/convertTemplate:Aircraft specs/convert
- Aspect ratio: 9.95
- Airfoil: NASA GA(W)-1Template:Aircraft specs/convertTemplate:Aircraft specs/convertTemplate:Aircraft specs/convert
- Fuel capacity: Template:Cvt in two integral wing tanksTemplate:Aircraft specs/convertTemplate:Aircraft specs/engTemplate:Aircraft specs/engTemplate:Aircraft specs/engTemplate:Aircraft specs/lengthTemplate:Aircraft specs/convert
- Propellers: 2-bladed W-530TA-D35Template:Aircraft specs/length
PerformanceTemplate:Aircraft specs/speedTemplate:Aircraft specs/speedTemplate:Aircraft specs/speedTemplate:Aircraft specs/speedTemplate:Aircraft specs/speedTemplate:Aircraft specs/rangeTemplate:Aircraft specs/rangeTemplate:Aircraft specs/rangeTemplate:Aircraft specs/convert
- g limits: +3.8 -1.52Template:Aircraft specs/convertTemplate:Aircraft specs/convertTemplate:Aircraft specs/convertTemplate:Aircraft specs/convertTemplate:Aircraft specs/convert
- Power/mass: Template:Cvt
- Take-off: Template:Cvt
- Landing: Template:Cvt
- Take-off to Template:Cvt: Template:Cvt
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See also
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References
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Further reading
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External links
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