Pegase Aero Pegazair-100 STOL
Tapanee Pegazair-100

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 its wing which has fixed leading edge slots, first flown in June 1991.

Zenair CH 701 STOL with the original Pega-STOL wing

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 skins. 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 aircraft was built as the Tapanee Pegazair-100 and the design was later developed into the four seat Tapanee Levitation 4.

Tapanee Pegazair-100 / slats extended

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:

P-80
Engine: Rotax 912
Seats: 2 side by side
Length: 22.5 ft
Wingspan: 29.0 ft
Wing area: 150 sq/ft
Max.flaps: 30 deg
MAUW: 1200 lbs
Empty Weight: 625 lbs
Usefull load: 575 lbs
VSO: 23 mph
Min.speed 50 % pwr: 15 mph
Cruise speed: 95 mph
VNE: 110 mph
Gross takeoff dist: 175 ft
Climb rate at Gross: 900 ft / min.
Usable fuel: 52 litres
Range: 325 milles
Ultimate Load: +6 -3,3 G

Pegazair-100 STOL
Engine: 1 × Continental O-200, 75 kW (100 hp)
Length: 6.83 m (22 ft 5 in)
Wingspan: 9 m (29 ft)
Wing area: 14 m2 (150 sq ft)
Airfoil: NACA 2415
Max.flaps: 30 deg
Empty weight: 374 kg (825 lb)
Gross weight: 658 kg (1,450 lb)
Usable Fuel capacity: 134 litres (29 imp gal; 35 US gal)
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)
Min.speed 50 % pwr: 18 mph
Gross takeoff dist: 300 ft
Climb rate at Gross: 800 ft / min.
Range: 1,014 km; 547 nmi (630 mi)
g limits: +6/-3.3
Wing loading: 47 kg/m2 (9.7 lb/sq ft)
Seats: 2 side by side

P-100
Engine: Rotax 914, 115 hp
Seats: 2 side by side
Length: 22.5 ft
Wingspan: 29.0 ft
Wing area: 150 sq/ft
Max.flaps: 30 deg
MAUW: 1350 lbs
Empty Weight: 760 lbs
Usefull load: 690 lbs
VSO: 28 mph
Min.speed 50 % pwr: 18 mph
Cruise speed: 115 mph
VNE: 125 mph
Gross takeoff dist: 225 ft
Climb rate at Gross: 950 ft / min.
Usable fuel: 134 litres
Range: 793 milles
Ultimate Load: +6 -3,3 G