Aero-Service Panda

Panda
Artist's rendering of the Panda
Role Ultralight aircraft
National origin Poland
Manufacturer Aero-Service Jacek Skopiński
First flight 28 September 2016
Status In production (2016)
Unit cost
€49,900 (Panda Standard, 2015)

The Aero-Service Panda is a Polish ultralight, 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 Panda was designed to comply with the Fédération Aéronautique Internationale microlight rules. It features a cantilever high-wing, a T-tail, a two-seats-in-side-by-side configuration enclosed cabin, fixed tricycle landing gear and a single engine in tractor configuration.[1][2][3][4]

The aircraft is made from sheet aluminum, with some parts, such as the engine cowling and wing tips made from composites. Its 8.91 m (29.2 ft) span wing employs a modified NACA 633-618 airfoil, has an area of 10.6 m2 (114 sq ft) and flaps. The cabin width is 120 cm (47 in).[1][2][3][4][5]

The Panda prototype was first flown on 28 September 2011.[2][3][4]

Operational history

Reviewer Marino Boric described the design in a 2015 review as possessing visibility that "is good in all directions because of very large glassed surfaces". He also noted that it is "sold at a reasonable price".[1]

Variants

Panda Standard
Base model powered by a 80 hp (60 kW) Rotax 912UL four-stroke powerplant.[1]
Panda Sport
Model powered by a 100 hp (75 kW) Rotax 912ULS four-stroke powerplant.[1]
Panda Exclusive
Model powered by a 100 hp (75 kW) Rotax 912ULS four-stroke powerplant plus with a Dynon glass cockpit and other options as standard.[1]

Specifications (Panda Standard)

Data from Tacke and manufacturer[1][5]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Length: 6.62 m (21 ft 9 in)
  • Wingspan: 8.91 m (29 ft 3 in)
  • Height: 2.32 m (7 ft 7 in)
  • Wing area: 10.6 m2 (114 sq ft)
  • Airfoil: modified NACA 633-618
  • Empty weight: 270 kg (595 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: 220 km/h (137 mph; 119 kn)
  • Cruise speed: 190 km/h (118 mph; 103 kn)
  • Stall speed: 62 km/h (39 mph; 33 kn) flaps down
  • Never exceed speed: 260 km/h (162 mph; 140 kn)
  • Range: 1,200 km (746 mi; 648 nmi) with 45 minutes reserves
  • Service ceiling: 3,650 m (11,980 ft)
  • g limits: +4/-2
  • Rate of climb: 6 m/s (1,200 ft/min)
  • Wing loading: 44.57 kg/m2 (9.13 lb/sq ft)

See also

References

  1. 1 2 3 4 5 6 7 8 Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015-16, page 20. Flying Pages Europe SARL, 2015. ISSN 1368-485X
  2. 1 2 3 4 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
  3. 1 2 3 4 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
  4. 1 2 3 4 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
  5. 1 2 Aero-Service Jacek Skopiński (2010). "Technical data and performance". Retrieved 17 December 2016.
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