Kappa 77 KP 2U-SOVA
| KP-2U Sova | |
|---|---|
 |
|
| KP-2U Skyleader 200 | |
| Role | Light aircraft |
| National origin | Czech Republic |
| Manufacturer | Kappa 77 a.s. Jilhavan Aircraft Skyleader a.s. ACS |
| First flight | 26 May 1996[1] |
| Status | In production |
| Number built | Over 210 by November 2010 |
| Unit cost |
Skyleader 150:
€66,100 flyaway, excluding tax (2010) |
The Kappa 77 KP-2U Sova, later produced as the Jihlavan KP-2U Skyleader and most recently as the Jihlavan Skyleader, is a two-seat civil utility aircraft designed in the Czech Republic and available in kit form for home building. It is a conventional low-wing monoplane featuring all-metal construction and tricycle undercarriage.
Contents
Design and development
Jilhavan Aircraft built the Kappa Sova for Kappa 77 from 1997 to 2004 and obtained marketing rights in 2005 when Kappa became insolvent. They became a subsidiary of Skyleader Aircraft in 2008 when the type was redesignated Jihlavan Skyleader. It is an all-metal design apart from a carbon fibre cockpit frame. It has two-spar tapered wings with 6° of dihedral, electrically operated Fowler flaps and upturned Küchemann tips. The fin and rudder are swept. The straight tapered tailplane is set on top of the fuselage, the port elevator carrying a trim tab.[2]
The Bulgarian company ACS started producing the Skyleader 600 at the state owned TEREM-Letets aircraft factory in Sofia in July 2015 under a licence agreement.[3]
The original Sova/Skyleader 150 has staggered side-by-side configuration seating with the starboard seat 200 mm (8 in) aft of the other, but a widened fuselage allows the Skyleader 200 to have true side-by-side seating. The earlier version has a forward-hinged canopy with fixed rear transparencies; the Skyleader 200 has a single-piece canopy. Both these variants normally have an electrically actuated tricycle undercarriage with a steerable nosewheel, though a fixed version is an option and is standard on the later Skyleader 500 and 600 variants. The standard engine for the 150/200 variants is a 60 kW (80 hp) Rotax 912UL, though the more powerful Rotax 912ULS or Rotax 914 can be fitted, all driving a choice of two-blade propellers. The 500/600 variants can also use the Rotax 912 UL or Rotax 912S; the Jabiru 2200 or 3300 engines may also be fitted. The Skyleader 500/600 variants have three-blade propellers.[2]
The Kappa 77 KP-2U Sova first flew on 26 May 1996 and the KP-5 Rapid 500 (later the Skyleader 500) in December 2003. Czech certification was achieved in September 1997 and March 2004 respectively. The Skyleader is produced in both kit and flyaway form.[2]
Operational history
Over 210 had been sold by November 2010. 145 Sovas and 12 Skyleaders appear on the civil registers of European countries, Russia excepted, in mid-2010.[4]
Variants (Jihlavan)
Data from Jane's All the World's Aircraft 2011/12[2]
- Skyleader 100
- Single-seat variant, with optional rectangular or trapezoidal wing planform and powered by a 64 hp (48 kW) Rotax 582 two-stroke engine. Was expected to be marketed starting in 2011 as a kit or complete aircraft.[5]
- KP-2U Skyleader 150
- Original the Kappa 77 KP-2U Sova. Staggered side-by-side seating.
- KP-2 Skyleader 200
- Introduced 1996, widened cockpit to 120 cm (47 in) for true side-by-side seating. It features retractable landing gear.[5]
- Rapid 200FC
- One-off hydrogen-powered via fuel cell and electric motor Skyleader 150 conversion, first flight 20 May 2010.
- KP-5 Skyleader 500
- S-LSA version, originally the KP-5 Rapid 500. FAA approved July 2005.[5][6]
- Skyleader 400
- Light-sport aircraft version with a gull-winged canopy and re-designed engine cowling, introduced as a "mid-line model".[7]
- Skyleader 600
- Light sport model introduced at AERO Friedrichshafen in 2010. It features a wider 128 cm (50 in) cockpit, revised wingtips and greater fuel capacity. Engines available include the 80 hp (60 kW) Rotax 912UL, the 100 hp (75 kW) Rotax 912ULS and the turbocharged 115 hp (86 kW) Rotax 914 four-stroke powerplants.[5]
Specifications (KP-2U Sova)
Data from Jane's All The World's Aircraft 2003–2004[1]
General characteristics
- Crew: one pilot
- Capacity: one passenger
- Length: 7.17 m (23 ft 6¾ in)
- Wingspan: 9.90 m (32 ft 5¾ in)
- Height: 2.60 m (8 ft 6¼ in)
- Wing area: 11.85 m² (127.6 ft²)
- Airfoil: NASA GA(W)-1 at root and GA(W)-2 at tip
- Empty weight: 285 kg (628 lb)
- Max. takeoff weight: 450 kg (990 lb)
- Powerplant: 1 × Rotax 912UL flat-four piston engine, two-blade propeller, 59.6 kW (79.9 hp)
Performance
- Maximum speed: 240 km/h (129 knots, 149 mph)
- Cruise speed: 200 km/h (108 knots, 124 mph)
- Stall speed: 48 km/h (26 knots, 30 mph)
- Range: 960 km (518 nmi, 596 mi)
- Rate of climb: 6.5 m/s (1,279 ft/min)
References
- ↑ 1.0 1.1 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 2.0 2.1 2.2 2.3 Lua error in package.lua at line 80: module 'strict' not found.
- ↑ Lua error in package.lua at line 80: module 'strict' not found.
- ↑ Lua error in package.lua at line 80: module 'strict' not found.
- ↑ 5.0 5.1 5.2 5.3 Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 76. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- ↑ Lua error in package.lua at line 80: module 'strict' not found.
- ↑ Lua error in package.lua at line 80: module 'strict' not found.
External links
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