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{|{{Infobox Aircraft Begin
{|{{Infobox aircraft begin
|name =PZL-105 Flaming
|name =PZL-105 Flaming
|image =Image:PZL105 Flaming PICT0049.JPG
|image = File:PZL105 Flaming PICT0049.JPG
|caption =PZL-105 at the [[Polish Aviation Museum]]
|caption =PZL-105 at the [[Polish Aviation Museum]]
}}{{Infobox Aircraft Type
}}{{Infobox aircraft type
|type =Utility aircraft
|type =Utility aircraft
|manufacturer =[[PZL|PZL Warszawa-Okęcie]]
|manufacturer =[[Państwowe Zakłady Lotnicze|PZL Warszawa-Okęcie]]
|designer =
|designer =
|first flight =9 November 1989
|first flight =9 November 1989
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|}
|}


'''PZL-105 Flaming''' ({{lang-en|[[Flamingo]]}}) is a [[Poland|Polish]] [[STOL|short-takeoff-and-landing]] (STOL) utility aircraft designed by [[PZL]] "Warszawa-Okęcie". It remained a prototype.
The '''PZL-105 Flaming''' (''flamingo'') is a Polish [[STOL|short-takeoff-and-landing]] (STOL) utility aircraft designed by [[Państwowe Zakłady Lotnicze|PZL]] "Warszawa-Okęcie". It remained a prototype.


==Development==
==Design and 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 aircraft|glider]] towing, [[parachute]] training, transport, [[air ambulance]], patrolling and [[Aerial application|crop dusting]] (with 500 kg of chemicals). Also a [[seaplane]] variant was intended.
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 aircraft|glider]] towing, [[parachute]] training, transport, [[air ambulance]], patrolling and [[Aerial application|crop dusting]] (with 500&nbsp;kg of chemicals). Also, a [[seaplane]] variant was intended.


The first prototype, powered with 265 kW (360 hp) Russian [[Vedeneyev M-14P|M-14P]] radial engine, was flown on 9 November [[1989 in aviation|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 O-720|Lycoming IO-720]]. It was flown on 27 July [[1991 in aviation|1991]] (markings SP-PRD). There was also made one prototype for static trials.
The first prototype, powered by a 265&nbsp;kW (360&nbsp;hp) Russian [[Vedeneyev M-14P|M-14P]] radial engine, was first flown on 9 November [[1989 in aviation|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&nbsp;kW (400&nbsp;hp) [[Lycoming O-720|Lycoming IO-720]]. It was flown on 27 July [[1991 in aviation|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 O-540|Lycoming I0-540]] flat engine instead.
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 O-540|Lycoming I0-540]] flat engine instead.


==Survivors==
==Design==
Metal construction braced high-wing monoplane, conventional in layout, [[duralumin]] covered. Semi-[[monocoque]] fuselage. Rectangular single-spar wings, fitted with Fowler [[Flap (aircraft)|flaps]] and slotted [[flaperon]]s. 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]].
The first prototype and the second prototype airframe (lacking engine) are in a collection of the [[Polish Aviation Museum]] in [[Kraków]].


==Specifications (PZL-105L)==
==Specifications (PZL-105M)==
{{Aircraft specs
===Description===
|ref=''Jane's All The World's Aircraft 1993-94.''<ref name="JAWA93-94">{{cite book |editor1-last=Lambert |editor1-first=Mark |editor2-last=Munson |editor2-first=Kenneth |editor3-last=Taylor |editor3-first=Michael J.H. |title=Jane's all the world's aircraft, 1993-94 |date=1993 |publisher=Jane's Information Group |location=London |isbn=0710610661 |pages=241–242 |edition= 84th}}</ref>
Metal construction braced high-wing monoplane, conventional in layout, [[duralumin]] covered. Semi-[[monocoque]] fuselage. Rectangular single-spar wings, fitted with Fowler [[Flap (aircraft)|flaps]] and slotted [[flaperon]]s. 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).
|prime units?=met
==Specifications (PZL-105L)==
<!--
{{aircraft specifications
General characteristics
<!-- if you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
-->
|plane or copter?=plane
|crew=1
|jet or prop?=prop
|capacity=5 pax / {{cvt|450|kg}} cargo
|ref=Jane's All The World's Aircraft 1993-94<ref name="Janes 93 p241-2"> Lambert 1993, pp. 241–242.</ref>
|length m=8.7
<!-- Now, fill out the specs. Please include units where appropriate (main comes first, alt in parentheses). If an item doesn't apply, like capacity, leave it blank. For additional lines, end your alt units with )</li> and start a new, fully-formatted line with <li> -->
|length note=<br />
|crew=1 pilot
::::'''PZL-105L''' {{cvt|8.67|m}}
|capacity=5
|span m=12.97
|length main=8.67 m
|height m=2.87
|length alt=28 ft 5¼ in
|wing area sqm=16.9
|span main=12.97 m
|aspect ratio=9.95
|span alt=42 ft 6½ in
|airfoil=NASA GA(W)-1
|height main=2.87 m
|empty weight kg=1130
|height alt=9 ft 5 in
|empty weight note=<br />
|area main=16.90 m²
::::'''PZL-105L''' {{cvt|1150|kg}}
|area alt=182 ft²
|empty weight main=1,150 kg
|gross weight kg=
|empty weight alt=2,535 lb
|max takeoff weight kg=1850
|fuel capacity={{cvt|270|L|USgal impgal}} in two integral wing tanks
|loaded weight main=
|more general=
|loaded weight alt=
<!--
|useful load main=
Powerplant
|useful load alt=
-->
|max takeoff weight main=1,850 kg
|eng1 number=1
|max takeoff weight alt=4,078 lb
|eng1 name=[[Vedeneyev M-14P]]
|more general='''Fuel''': 270 L (71.3 US Gallons)
|eng1 type=9-cylinder air-cooled radial piston engine
|engine (prop)=[[Lycoming O-720|Lycoming IO-720]]-A1B
|eng1 kw=268.5
|type of prop= air-cooled [[flat engine]]
|eng1 note=<br />
|number of props=1
::::'''PZL-105L''' {{cvt|298|kW}} [[Lycoming IO-720-A1B]]
|power main=298 kW
|power alt=400 hp
|max speed main=260 km/h
|max speed alt= 140 knots, 162 mph
|max speed more=
|cruise speed main= 216 km/h
|cruise speed alt=117 knots, 134 mph
|cruise speed more=(econ cruise)
|stall speed main= 102 km/h
|stall speed alt= 55 knots, 64 mph
|never exceed speed main=306 km/h
|never exceed speed alt=165 knots, 190 mph
|range main=981 km
|range alt= 529 nm, 609 mi
|range more=at econ cruise speed
|ceiling main=5,070 m
|ceiling alt= 16,625 ft
|climb rate main=5.6 m/s
|climb rate alt=1,100 ft/min
|loading main=109 kg/m²
|loading alt=22.4 lb/ft²
|power/mass main=0.161 kW/kg
|power/mass alt=0.0982 hp/lb
|more performance=
|armament=


|prop blade number=2
|prop name=W-530TA-D35
|prop dia m=2.4
|prop dia note=constant-speed propeller
::::'''PZL-105L''' 3-bladed {{cvt|2.18|m}} diameter [[Hartzell Propeller|Hartzell]] constant-speed propeller
<!--
Performance
-->
|max speed kmh=245
|max speed note=<br />
::::'''PZL-105L''' {{cvt|260|km/h|mph kn}}
|cruise speed kmh=205
|cruise speed note=max
:::{{cvt|188|km/h|mph kn}} economical
::::'''PZL-105L''' {{cvt|235|km/h|mph kn}} max
::::'''PZL-105L''' {{cvt|216|km/h|mph kn}} economical
|stall speed kmh=102
|stall speed note=flaps down engine idling
|never exceed speed kmh=306
|minimum control speed kmh=
|range km=1044
|range note=at max cruising speed
:::{{cvt|1085|km|mi nmi}} at economical cruise speed
::::'''PZL-105L''' {{cvt|853|km|mi nmi}} at max cruising speed
::::'''PZL-105L''' {{cvt|981|km|mi nmi}} at economical cruise speed
|combat range km=
|ferry range km=
|endurance=<!-- if range unknown -->
|ceiling m=4140
|ceiling note=<br />
::::'''PZL-105L''' {{cvt|5070|m}}
|g limits=<big>+</big>3.8 <big>-</big>1.52
|roll rate=<!-- aerobatic -->
|climb rate ms=5.5
|climb rate note=at sea level
::::'''PZL-105L''' {{cvt|5.6|m/s|ft/min}}
|time to altitude=
|wing loading kg/m2=109.5
|fuel consumption kg/km=
|power/mass={{cvt|0.145|kW/kg|hp/lb}}
::::'''PZL-105L''' {{cvt|0.161|kW/kg|hp/lb}}
|more performance=<br />
*'''Take-off:''' {{cvt|176|m}}
*'''Landing:''' {{cvt|153|m}}
*'''Take-off to {{cvt|50|m}}:''' {{cvt|338|m}}
*'''Landing from {{cvt|50|m}}:''' {{cvt|326|m}}
::'''PZL-105L'''
:::*'''Take-off:''' {{cvt|189|m}}
:::*'''Landing:''' {{cvt|157|m}}
:::*'''Take-off to {{cvt|50|m}}:''' {{cvt|351|m}}
:::*'''Landing from {{cvt|50|m}}:''' {{cvt|330|m}}
}}
}}


==See also==
==See also==
{{Portal|Poland|Aviation}}
{{aircontent|
{{aircontent|
|related=
|related=
*[[PZL-104 Wilga]]
* [[PZL-104 Wilga]]
|similar aircraft=
|similar aircraft=
|lists=<!-- related lists -->
|lists=<!-- related lists -->
Line 104: Line 135:
==References==
==References==
{{Reflist}}
{{Reflist}}

*Andrzej Glass: ''Samoloty '94'', Grupa IMAGE, Warsaw 1994, ISBN 83-85461-19-1
==Further reading==
* Lambert, Mark (ed.). ''Jane's All The World's Aircraft 1993-94''. Coulsdon, UK: Jane's Data Division, 1993. ISBN 0 7106 1066 1.
* {{cite book |editor1-last=Taylor |editor1-first=John W.R. |editor2-last=Munson |editor2-first=Kenneth |editor3-last=Taylor |editor3-first=Michael J.H. |title=Jane's all the world's aircraft, 1989-90 |date=1989 |publisher=Jane's Information Group |location=London |isbn=0710608969 |pages=203–204 |edition= Eightieth birthday }}
* {{cite book |last1=Glass |first1=Andrzej |title=Samoloty '94 |date=1994 |publisher=Grupa IMAGE |location=Warsaw |isbn=83-85461-19-1}}


==External links==
==External links==
{{commons category|PZL-105 Flaming}}
*[http://lotnictwo.net/galselect.php?p=0&ui=133&mi=52&quer=1=1&ti=296&selectby=fotoID%20DESC&wpis= Photos at Lotnictwo.net]
*[http://lotnictwo.net/galselect.php?p=0&ui=133&mi=52&quer=1=1&ti=296&selectby=fotoID%20DESC&wpis= Photos at Lotnictwo.net]
{{PZL aircraft}}
{{aviation lists}}


{{PZL aircraft}}
[[Category:Polish civil utility aircraft 1980-1989]]
[[Category:STOL|PZL-105]]


[[Category:1980s Polish civil utility aircraft]]
[[hu:PZL–105 Flaming]]
[[Category:PZL aircraft]]
[[Category:Single-engined tractor aircraft]]
[[Category:High-wing aircraft]]
[[Category:Aircraft first flown in 1989]]

Revision as of 07:47, 9 August 2023

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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