Polish ultralight aircraft
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]
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
^ a b c d e Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015–16 , page 20. Flying Pages Europe SARL, 2015. ISSN 1368-485X
^ a b c d 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
^ a b c d e 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
^ a b c d 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
^ a b Aero-Service Jacek Skopiński (2010). "Technical data and performance" . Retrieved 17 December 2016 .
External links