PERFORMANCE
AND
SPECIFICATIONS
| SPECIFICATIONS |
STOL CH 750 |
|
(Based on factory prototype, equipped with
100-hp Continental O-200
powerplant) |
| WING SPAN |
29 FT. 9 In. |
9.1 m. |
| HEIGHT (rudder tip) |
8 Ft.
8 In. |
2.6 m. |
| WING AREA |
144 SQ.FT. |
13.4 m.sq. |
|
WING CHORD |
4 Ft. 10 In. |
1.5 m. |
| LENGTH |
21 Ft. 10 In. |
6.7 m. |
|
HORIZONTAL TAIL SPAN |
8 Ft. 5 In. |
2.6 m. |
|
HORIZONTAL TAIL AREA |
22.2 Sq. Ft. |
2.0 m.sq. |
| EMPTY WEIGHT |
775 LBS. |
350 kg. |
| GROSS WEIGHT |
1,320 LBS. |
600 kg. |
| USEFUL LOAD |
545 LBS. |
250 kg. |
| WING LOADING |
9.15 LBS/FT² |
44.8 m² |
| POWER LOADING |
13.2 LBS/BHP |
6.0 kg/BHP |
| DESIGN LOAD FACTOR (ultimate) |
+6 G / -3G |
| CABIN WIDTH (shoulders) |
42 INCHES |
100 cm. |
|
CABIN WIDTH (optional bubble
doors) |
50 INCHES |
1.27
m. |
| FUEL CAPACITY (std., dual wing tanks) |
24 US Gallons
(2 x 12 gal.) |
90 liters
(2 x 45 liters) |
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| STOL
CH 750 PERFORMANCE |
Continental O-200 - 100 hp |
|
@ gross weight |
| TAKE-OFF ROLL |
100 Feet |
30 m. |
| LANDING ROLL |
125 Feet |
38 m. |
|
MAX. CRUISE, Sea Level |
100 MPH |
162 km/h |
|
VNE |
125
MPH |
200 km/h |
| STALL,
flaps down |
35 MPH |
56 km/h |
| RATE OF CLIMB |
1,000
fpm |
5.1 m/s |
| SERVICE CEILING |
14,000+
feet |
4,200+ m. |
| STD. RANGE |
400 miles |
710 km. |
| ENDURANCE |
5 Hours |
5 Hours |
Specification and
performance figures quoted with the
Continental O-200-A engine (100 HP).
Standard atmosphere, sea level, no wind.
Performance and specification figures based on prototype flight test
results. All technical data,
specification and performance figures subject to change without notice.
Powerplant range: 80 - 125 HP engines.
Different engines and installed options will affect performance and
specification figures. Heavier engines will limit useful load (by
increasing the empty weight).
Engine Limitations:
80 - 125 hp, up to 300
lbs. installed. 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.
While the STOL CH 750 was developed to meet
the definition of a light-sport aircraft, as defined in the FAA's
Sport Pilot
category, Zenith Aircraft Company cannot guarantee that the aircraft, as
constructed by the builder, will meet the definition. Due to the gross
weight limitations of the Sport Pilot / Light-Sport Aircraft category,
it is recommended that the aircraft be kept as light as possible
if planning to operate the aircraft in this category. Larger and heavier
engines and other installed equipment limit the useful load of the
aircraft, and may disqualify the aircraft from meeting the defined
category limits of the Sport Pilot category.
 |
STOL CH 750
True short take-off and landing
capability for
the serious sport pilot. |
|
