Tapanee Pegazair 100

Development

Development of the Pegazair started in 1985 by Serg Dufour of Mont-Saint-Michel, Quebec. Originally it consisted of a new set of Pega-STOL wings with retractable leading edge slats to be installed on Zenair CH 701 STOLs to replace their wings which have fixed leading edge slots. Dufour went on to develop a new fuselage and tail to match the wings. The Pegazair is a two seats in side-by-side configuration, strut-braced, high-wing monoplane with conventional landing gear. Fuselage construction is welded steel tubing with aluminum skin. The wings employ full length flaperons and leading edge slats that deploy automatically. The tailplane is slotted for slow speed authority. The prototype was outfitted with a 65 hp (48 kW) Continental A-65 engine.

The design was later developed into the four-seat Tapanee Levitation 4.

Variants

Pegazair P80

Powered by a 80 hp (60 kW) Rotax 912UL

Pegazair P100

Powered by a 80 hp (60 kW) Continental O-200 or 115 hp (86 kW) Rotax 914

Specifications (Pegazair-100 STOL)

Data from Manufacturer and Kitplanes

General characteristics

Crew: one

Capacity: one passenger

Length: 6.83 m (22 ft 5 in)

Wingspan: 8.8 m (29 ft)

Wing area: 14 m² (150 sq ft)

Airfoil: NACA 2415

Empty weight: 374 kg (825 lb)

Gross weight: 658 kg (1,450 lb)

Fuel capacity: 134 litres (29 imp gal; 35 US gal)

Powerplant: 1 × Continental O-200 horizontally opposed piston, 75 kW (100 hp)

Performance

Cruise speed: 169 km/h; 91 kn (105 mph)

Stall speed: 45 km/h; 24 kn (28 mph)

Never exceed speed: 201 km/h; 109 kn (125 mph)

Range: 1,014 km; 547 nmi (630 mi)

g limits: +6/-3.3

Wing loading: 47 kg/m² (9.7 lb/sq ft)