- Chase-Sisley C100-S
C100-S Role Glider National origin United States Designer Robert Chase First flight 1968 Introduction 1968 Status No longer in production Number built One
Design and development
The aircraft is built from a combination of wood, styrofoam, aluminium and fiberglass. The semi-tapered wing is built from wood and styrofoam, covered with stress-bearing fiberglass. The wing is tapered outboard of the mid-span point. The wing spar is built up from 14 layers of fiberglass and epoxy resin at the root and is a box-style spar that occupies 40% of the wing chord. The wing is constructed in three pieces, a center-section and wing tips and features Schempp-Hirth dive brakes. The wing is 15% thick and employs a NACA 64(3)-615 laminar flow airfoil.
The fuselage is built from aluminium and features stressed skin construction. The landing gear is a fixed monowheel. The pilot's seating position is semi-reclined. In addition to the dive brakes the pilot has a tail-mounted drag chute available.
- Crew: one
- Wingspan: 55 ft (17 m)
- Wing area: 138 sq ft (12.8 m2)
- Aspect ratio: 22:1
- Airfoil: NACA 64(3)-615
- Empty weight: 530 lb (240 kg)
- Gross weight: 730 lb (331 kg)
- Maximum glide ratio: 38:1 at 55 mph (88 km/h)
- Rate of sink: 120 ft/min (0.61 m/s) at 48 mph (77 km/h)
- Wing loading: 5.3 lb/sq ft (26 kg/m²)
- ^ a b c d e f Activate Media (2006). "C100-S Chase-Sisley". http://www.sailplanedirectory.com/PlaneDetails.cfm?PlaneID=51. Retrieved 6 May 2011.
- ^ a b c d e f g Said, Bob: 1983 Sailplane Directory, Soaring Magazine, page 39. Soaring Society of America November 1983. USPS 499-920
- ^ a b Federal Aviation Administration (May 2011). "Make / Model Inquiry Results". http://registry.faa.gov/aircraftinquiry/NNum_Results.aspx?NNumbertxt=2160. Retrieved 15 May 2011.
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