PZL-105 Flaming
PZL-105 Flaming (English: 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 a successful utility aircraft PZL-104 Wilga, more modern and economical and offering increased transport capacity. The design was initially called Wilga 88. It retained high-wing layout of the PZL-104 and side doors opening upwards, but it is a completely new plane. Comparing to the Wilga, it has six-place cab instead of four-place and wings are supported with 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 with 265 kW (360 hp) Russian M-14P radial engine, was 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 1980s and 1990s, connected with a change of political system in Poland, and a priority of PZL-130 Orlik trainer program, caused, that the Flaming program was suspended and the production has not started. The factory developed a new variant of 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, in three rows, 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).
Survivors
The first prototype and the second prototype airframe (lacking engine) are in a collection of the Polish Aviation Museum in Kraków.
Specifications (PZL-105L)
Data from Jane's All The World's Aircraft 1993-94[1]
General characteristics
- Crew: 1 pilot
- Capacity: 5
- Length: 8.67 m (28 ft 5¼ in)
- Wingspan: 12.97 m (42 ft 6½ in)
- Height: 2.87 m (9 ft 5 in)
- Wing area: 16.90 m² (182 ft²)
- Empty weight: 1,150 kg (2,535 lb)
- Max. takeoff weight: 1,850 kg (4,078 lb)
- Powerplant: 1 × Lycoming IO-720-A1B air-cooled flat engine, 298 kW (400 hp)
- Fuel: 270 L (71.3 US Gallons)
Performance
- Never exceed speed: 306 km/h (165 knots, 190 mph)
- Maximum speed: 260 km/h (140 knots, 162 mph)
- Cruise speed: 216 km/h (117 knots, 134 mph) (econ cruise)
- Stall speed: 102 km/h (55 knots, 64 mph)
- Range: 981 km (529 nm, 609 mi)at econ cruise speed
- Service ceiling: 5,070 m (16,625 ft)
- Rate of climb: 5.6 m/s (1,100 ft/min)
- Wing loading: 109 kg/m² (22.4 lb/ft²)
- Power/mass: 0.161 kW/kg (0.0982 hp/lb)
See also
- Related development
References
- ↑ Lambert 1993, pp. 241–242.
- Andrzej Glass: Samoloty '94, Grupa IMAGE, Warsaw 1994, ISBN 83-85461-19-1
- Lambert, Mark (ed.). Jane's All The World's Aircraft 1993-94. Coulsdon, UK: Jane's Data Division, 1993. ISBN 0-7106-1066-1.
External links
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