The Centrair C101 Pegase is a Standard Class single-seat glider manufactured by Centrair starting in 1981. The design uses the ASW 19 fuselage with a new wing designed by ONERA,[1] giving better performance than the German original.
| C101 Pegase | |
|---|---|
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| General information | |
| Type | Standard Class sailplane |
| Manufacturer | Centrair |
| Designer | Marc Ranjon |
| Number built | ~700 |
Models manufactured since 1990 as the Pegase 90 are equipped with a different cockpit interior: Shorter handles, smaller instrument panel and minor structural changes. The major difference between the Pegase 90 and previous models was the introduction of flight controls that automatically connect during rigging.
The aircraft structure is composed of laminated fibreglass and epoxy resin. The wing has a laminar flow airfoil with top surface air brakes.
Variants
edit- Centrair 101 Pegase
- Prototype Pegase with ASW19-derived fuselage with all-new wings.
- C101
- Fitted with fixed landing gear
- C101A
- Fitted with retractable landing gear
- C101P
- Fitted with fixed landing gear and fittings for optional winglets
- C101AP
- Fitted with retractable landing gear and fittings for optional winglets
- C101B
- Fitted with CFRP main spar allowing additional water ballast to be carried
- C101D
- Altered wing shape, increasing performance
- C101BC
- Altered wing shape and CFRP main spar
Specifications (Pégase D)
editData from [2]
General characteristics
- Crew: 1
- Length: 7 m (23 ft 0 in)
- Wingspan: 15 m (49 ft 3 in)
- Height: 1.38 m (4 ft 6 in)
- Wing area: 10.5 m2 (113 sq ft)
- Aspect ratio: 21.43
- Airfoil: root: ONERA COAP1; tip:ONERA COAP2
- Empty weight: 252 kg (556 lb)
- Max takeoff weight: 505 kg (1,113 lb)
Performance
- Never exceed speed: 250 km/h (160 mph, 130 kn) in smooth air at max t/o weight
- 170 km/h (92 kn; 110 mph) in rough air (Serial Nos 101001 to 101039plus 101041, which have not had Centrair Major Mod 101-02, ( DGAC AD 93-145(A)) incorporated, have Vra, decreased to 163 km/h / 88 knots.)
- 170 km/h (92 kn; 110 mph) on aero-tow
- 120 km/h (65 kn; 75 mph) on winch launch
- Maximum glide ratio: 42.5 at 105 km/h (57 kn; 65 mph) at max t/o weight
- Rate of sink: 0.62 m/s (122 ft/min) at 85 km/h (46 kn; 53 mph) at max t/o weight
- Wing loading: 48.1 kg/m2 (9.9 lb/sq ft) max
See also
editRelated lists
References
edit- ^ Chabbert, Bernard. "La Recherche". Gliding Research No. 14. Archived from the original on 2017-07-28. Retrieved 2017-04-12.
- ^ John W.R. Taylor, ed. (1988). Jane's All the World's Aircraft 1988-89. London: Jane's Information Group. pp. 619–620. ISBN 0-7106-0867-5.
Further reading
edit- Simons, Martin (2005). Sailplanes 1965-2000 (2nd revised ed.). Königswinter: EQIP Werbung und Verlag G.m.b.H. ISBN 978-3-9808838-1-8.
External links
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