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PERFORMANCE
AND SPECIFICATIONS
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).
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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. |
DESIGN LIMITATIONS:
| 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. Zenith Aircraft Company does
not manufacture or directly support engines.
Large Views:
Side |
Front |
Top
PERFORMANCE
Lycoming O-360, 180-hp |
Typical Load: 500
Lbs
1,650 Lbs. |
Gross Weight
2,150 Lbs. |
| TAKE-OFF ROLL |
290 Ft. |
88 m. |
390 Ft. |
119 m. |
| MAX LEVEL SPEED |
112 MPH |
181 km/h |
110 MPH |
178 km/h |
CRUISE SPEED
(75% power @ 7,000 Ft.) |
106 MPH |
170 km/h |
105 MPH |
169 km/h |
| STALL SPEED (Flaps Down) |
35 MPH |
56 km/h |
39 MPH |
64 km/h |
| STALL SPEED (Flaps Up) |
43 MPH |
69 km/h |
48 MPH |
77 km/h |
| RATE OF CLIMB |
1,200 FPM |
6.1 m/s |
720 FPM |
3.7 m/s |
| SERVICE CEILING |
16,000+ Ft. |
4,875+ m. |
14,000 Ft |
4,267 m. |
| ENDURANCE (Standard) |
3.0 Hrs. |
3.0 Hrs. |
| ENDURANCE (Extended Range Option) |
6.0 Hrs. |
6.0 Hrs. |
| RANGE (Standard) |
320 Miles |
515 km. |
315 Miles |
507 km. |
| RANGE (Extended Range Option) |
640 Miles |
1,030 km. |
630 Miles |
1,015 km. |
Above performance figures with the
Lycoming O-360-A engine (180 BHP: 400 lbs. with accessories and fixed-pitch
Sensenich 76-EM8-0-54 metal propeller). Standard atmosphere, sea level, no
wind. All technical data, specification and performance figures subject to
change without notice.
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Click here to view sample Weight & Balance / Loading worksheet (pdf
document). |
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Click here to view a short video clip of a STOL CH 801 take-off.
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