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The following performance and specification figures are based on the production prototype STOL CH 801 equipped with the Lycoming O-360-A engine (180 BHP: 400 lbs. with accessories and fixed-pitch Sensenich 76-EM8-0-54 metal propeller).
| SPECIFICATIONS | STOL CH 801 | |
| LENGTH | 24 Ft. 6 In. | 7.5 m. |
| HEIGHT | 10 Ft. 0 In. | 3.0 m. |
| WING SPAN | 31 Ft. 4 In. | 9.55 m. |
| WING AREA | 167 SQ.FT. | 15.5 m.sq. |
| WING CHORD | 5 Ft. 3 In. | 1.6 m. |
| HORIZONTAL TAIL SPAN | 10 Ft. 1 In. | 3.1 m. |
| HORIZONTAL TAIL AREA | 30 SQ.FT. | 2.8 m.sq.. |
| EMPTY WEIGHT | 1,150 LBS. | 522 kg. |
| DESIGN GROSS WEIGHT | 2,200 LBS. | 1,000 kg. |
| USEFUL LOAD | 1,050 LBS. | 478 kg. |
| FUEL CAPACITY (Standard) - Fuel weight (Standard) |
30 Gal. (2 x 15) = 176 LBS. |
112 l. (2 x 56) = 80 kg. |
| FUEL CAPACITY (Extended Range Option) - Fuel weight (Extended Range Option) |
60 Gal. (4 x 15) = 352 LBS. |
224 l. (4 x 56) = 160 kg. |
| DESIGN PAYLOAD - Occupants + Baggage / Cargo |
800 LBS. = 200 lbs X 4 |
360 kg. = 90 kg. X 4 |
| WING LOADING | 12.9 LBS/FT² | 62.9 kg/m² |
| POWER LOADING | 11.95 LBS/BHP | 5.44 kg/BHP |
| CABIN WIDTH | 44 INCHES | 112 cm. |
| CABIN LENGTH | 78 INCHES | 198 cm. |
PLEASE NOTE: Empty weights will vary depending on engine used and propeller type, instruments, avionics, upholstery, accessories and options chosen by the builder as well as amount of paint used.
| DESIGN LIMITS | ||||||||||||||||||||||||||
| POWER | 150 - 240 BHP. | |
| MAX. INSTALLED POWERPLANT WEIGHT | 440 lbs. | 200 kg. |
| MAX. TAKE-OFF WEIGHT (MTOW) | 2,200 lbs. | 998 kg. |
| DESIGN LOAD FACTOR (ultimate) @ 2,200 lbs. | + 5.7, - 2.8 | |
| MAX. WING LOADING (@ 2,200 lbs.) | 13.2 PSF | 64.4 kg/m² |
| MAX. FLAP EXTENDED SPEED | 80 MPH | 129 km/h |
| MAX. CRUISE SPEED - VC | 120 MPH | 193 km/h |
| NEVER EXCEED SPEED (VNE) | 150 MPH | 240 km/h |
Technical data, specification
and performance figures subject to change without notice. Alternative
engines will affect performance, specifications and flight characteristics
of the aircraft. Also, the weight and balance of the aircraft may be
adversely affected by alternative engines, and the original fuel system
may not be adequate or suitable for some engines. Most alternative engines
will require a custom engine mount and engine cowl. Zenair Ltd. does not manufacture or directly support engines.
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- Click here to view sample Weight & Balance / Loading worksheet (pdf document).
