Zenair CH 100
| Mono-Z CH 100 | |
|---|---|
| |
| Role | Homebuilt light aircraft |
| National origin | Canada |
| Manufacturer | Zenair |
| Designer | Chris Heintz |
| First flight | 8 May 1975 |
| Developed from | Zenair CH 200 |
The Zenair Mono-Z CH 100 is a single-seat, single-engined Canadian light aircraft of the 1970s, that was designed by Chris Heintz. It is a smaller version of the Zenair CH 200 with a less powerful engine, which was sold as a homebuilt aircraft by Zenair.
Development and design
[edit]After emigrating to Canada and setting up Zenair to sell plans and kits for amateur construction of his Zenith two-seat-light aircraft, the German aircraft designer Chris Heintz started design of a smaller, single-seat development of the Zenith, the Mono-Zenith.[1] The Mono-Z CH 100 is similar to the Zenith that preceded it, a low-winged cantilever monoplane of all metal construction. The aircraft features a large cockpit for taller pilots, with a pilot and baggage combined weight allowance of 240 lb (109 kg) and removable wings for storage and towing the aircraft behind a car. The factory claimed a build time of 600 hours. It is designed to be powered by engines from 45 to 100 hp (33.5 to 74.5 kW).[2][3]
The first CH 100 made its maiden flight on 8 May 1975, powered by a 55 hp (41 kW) Volkswagen air-cooled engine of 1600 cc, with 110 sets of plans and kits sold by 1982.[4] Zenair continued to produce kits until 1988.[5]
Operational history
[edit]A total of three CH 100s were registered in Canada since 1987 and none are registered in 2010.[6]
Specifications (65 hp engine)
[edit]Data from Jane's All The World's Aircraft 1988-89[7]
General characteristics
- Crew: 1
- Length: 19 ft 6 in (5.94 m)
- Wingspan: 22 ft 0 in (6.71 m)
- Height: 6 ft 6 in (1.98 m)
- Wing area: 91.5 sq ft (8.50 m2)
- Aspect ratio: 5.28:1[4]
- Airfoil: GAW-1 (modified)
- Empty weight: 630 lb (286 kg)
- Max takeoff weight: 960 lb (435 kg)
- Fuel capacity: 14.4 US Gallons (55 L)
- Powerplant: 1 × Volkswagen , 65 hp (48 kW)
Performance
- Maximum speed: 125 mph (201 km/h, 109 kn)
- Cruise speed: 110 mph (180 km/h, 96 kn)
- Stall speed: 48 mph (77 km/h, 42 kn)
- Range: 400 mi (640 km, 350 nmi) with maximum fuel
- Service ceiling: 12,000 ft (3,700 m)
- Rate of climb: 820 ft/min (4.2 m/s)
See also
[edit]Related development
Notes
[edit]- ^ Taylor 1976, p.458.
- ^ Taylor 1982, pp. 493–494.
- ^ Zenair, Zenair pamphlet, circa 1986.
- ^ a b Taylor 1982, p.494.
- ^ Chris Heintz:Light Aircraft Design History Archived July 19, 2011, at the Wayback Machine. zenair-deutschland.de. Retrieved 28 February 2010.
- ^ Transport Canada (February 2010). "Canadian Civil Aircraft Register Historical Information". Archived from the original on 2010-04-11. Retrieved 2010-02-28.
- ^ Taylor 1988, p.514.
References
[edit]- Taylor, John W. R. Jane's All The World's Aircraft 1976-77. London:Jane's Yearbooks, 1976. ISBN 0-354-00538-3.
- Taylor, John W. R. Jane's All The World's Aircraft 1982-83. London:Jane's Yearbooks, 1982. ISBN 0-7106-0748-2.
- Taylor, John W. R. Jane's All The World's Aircraft 1988-89. Coulsdon, UK:Jane's Defence Data, 1988. ISBN 0-7106-0867-5.