avia.wikisort.org - Aeroplane
The Aero-Service Puma is a Polish ultralight aircraft, designed and produced by Aero-Service Jacek Skopiński of Warsaw. The aircraft is supplied complete and ready-to-fly.[1][2][3][4]
| Puma | |
|---|---|
 | |
| Artist's rendering of the Puma | |
| Role | Ultralight aircraft |
| National origin | Poland |
| Manufacturer | Aero-Service Jacek Skopiński |
| First flight | pending |
| Status | Under development (2016) |
Design and development
The Puma was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a cantilever low-wing, a two-seats-in-side-by-side configuration enclosed cockpit under a bubble canopy, retractable tricycle landing gear and a single engine in tractor configuration.[1][2][3][4]
The aircraft fuselage is made from welded steel tubing, with an aluminum sheet wing. Its 9.15 m (30.0 ft) span wing employs a NACA 4415 airfoil at the wing root, transitioning to a NACA 4412 at the wing tip. The wing has an area of 11.3 m2 (122 sq ft) and mounts flaps. Standard engines available are the 80 hp (60 kW) Rotax 912UL, the 100 hp (75 kW) Rotax 912ULS and the 115 hp (86 kW) Rotax 914 four-stroke powerplants. The cabin width is 124 cm (49 in).[1][2][3][4][5]
The Puma was designed in 2008, with a prototype under construction in September 2011. No first flight of the design has been confirmed.[2][3][4]
A fixed gear version, to be called the Raptor, was under preliminary development in 2010.[1][3]
Specifications (Puma)
Data from Tacke and manufacturer[1][5]
General characteristics
- Crew: one
- Capacity: one passenger
- Length: 6.27 m (20 ft 7 in)
- Wingspan: 9.15 m (30 ft 0 in)
- Height: 2.30 m (7 ft 7 in)
- Wing area: 11.3 m2 (122 sq ft)
- Airfoil: Root: NACA 4415, tip: NACA 4412
- Empty weight: 290 kg (639 lb)
- Gross weight: 472.5 kg (1,042 lb)
- Fuel capacity: 100 litres (22 imp gal; 26 US gal)
- Powerplant: 1 × Rotax 912UL four cylinder, liquid and air-cooled, four stroke aircraft engine, 60 kW (80 hp)
- Propellers: 3-bladed composite
Performance
- Maximum speed: 240 km/h (150 mph, 130 kn)
- Cruise speed: 220 km/h (140 mph, 120 kn)
- Stall speed: 61 km/h (38 mph, 33 kn) flaps down
- Never exceed speed: 270 km/h (170 mph, 150 kn)
- Range: 1,200 km (750 mi, 650 nmi) with 45 minute reserve
- Service ceiling: 3,650 m (11,980 ft)
- g limits: +4/-2
- Rate of climb: 8 m/s (1,600 ft/min)
- Wing loading: 51.63 kg/m2 (10.57 lb/sq ft)
See also
References
- Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015–16, page 20. Flying Pages Europe SARL, 2015. ISSN 1368-485X
- Jackson, Paul (ed): Jane's All The World's Aircraft 2012–2013, pages 500–501. Jane's Information Group, 2012. ISBN 978 0 7106 30001
- Jackson, Paul (ed): IHS-Jane's All The World's Aircraft 2013–2014, Development and Production, pages 502–504. Jane's Information Group, 2013. ISBN 978 0 7106 30407
- Jackson, Paul (ed): IHS-Jane's All The World's Aircraft 2014-2015, Development and Production, pages 520–521. Jane's Information Group, 2014. ISBN 978-0710631350
- Aero-Service Jacek Skopiński (2010). "Technical data and performance". Retrieved 17 December 2016.
External links
Другой контент может иметь иную лицензию. Перед использованием материалов сайта WikiSort.org внимательно изучите правила лицензирования конкретных элементов наполнения сайта.
WikiSort.org - проект по пересортировке и дополнению контента Википедии