Teknisk informasjon

SPESIFIKASJONER STOL CH 701
VINGEBREDDE 27 FEET 8.2 m.
VINGESPENN 122 SQ.FT. 11.4 m.sq.
LENGDE 20 Ft. 11 In. 6.38 m.
HØYDE (siderortupp) 8 Ft. 7 In. 2.6 m.
TOMVEKT 580 LBS. 263 kg.
MAKSVEKT 1,100 LBS. 500 kg.
NYTTELAST 520 LBS. 236 kg.
VINGE 9.0 LBS/FT² 43.8 m²
VINGELAST 13.75 LBS/BHP 6.25 kg/BHP
DESIGN LASTE FAKTOR(ultimate) +6 G / -3G
KABINBREDDE (skuldre) 40 INCHES 100 cm.
CABIN BREDDE (mulighet bubble doors) 44 INCHES 110 cm.
BENSINTANKER (std., to vingetanker) 20 US Gallons
(2 x 10 gal.)
76 liters
(2 x 38 liters)

 

STOL CH 701 PERFORMANCE ROTAX 912 (80 HP) ROTAX 912S (100 HP)
  SINGLE DUAL SINGLE DUAL
TOP SPEED (MPH) 85 85 95 95
CRUISE, Sea Level (MPH) 80 80 85 85
75% CRUISE @ 8,000 ft. (TAS*) 92 92 98 98
VNE (MPH) 110 110 110 110
STALL (MPH) 28 30 28 30
RATE OF CLIMB (FPM) 1,100 1,000 1,200 1,100
TAKE-OFF ROLL (FEET) 60 115 50 90
LANDING ROLL (FEET) 80 140 80 140
SERVICE CEILING (FEET) 13,000+ 12,000+ 15,000+ 12,000+
STD. RANGE (MILES) 372 372 350 350
ENDURANCE  4.6 Hrs. 4.6 Hrs. 4.1 Hrs. 4.1 Hrs.

 

Prestasjoner og tekn.data

Følgende data baserer seg på bruk prototypen til 801 med en Lycoming O-360-A motor (180hk : 180 kg) med utstyr og med en pix-pitch 76-EM 8-054 metall propell.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
LENGDE 24 Ft. 6 In. 7.5 m.
HØYDE 10 Ft. 0 In. 3.0 m.
VINGESPENN 31 Ft. 4 In. 9.55 m.
VING AREAL 167 SQ.FT. 15.5 m.sq.
VING CHORDE 5 Ft. 3 In. 1.6 m.
HALE BREDDE 10 Ft. 1 In. 3.1 m.
HALE AREAL 30 SQ.FT. 2.8 m.sq..
TOMVEKT 1,150 LBS. 522 kg.
MAXVEKT 2,200 LBS. 1,000 kg.
NYTTELAST 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.
BENSIN (utvidet tankvolum mulighet)
- Bensin vekt (Utvidet tank mulighet)
60 Gal. (4 x 15)
= 352 LBS.
224 l. (4 x 56)
= 160 kg.
DESIGN MAXVEKT- 2personer + Baggasje / last 800 LBS.
= 200 lbs X 4
360 kg.
= 90 kg. X 4
VINGE LAST 12.9 LBS/FT² 62.9 kg/m²
POWER LOADING 11.95 LBS/BHP 5.44 kg/BHP
COCPIT BREDDE 44 INCHES 112 cm.
COCPIT LENGDE 78 INCHES 198 cm.


Designbegrensinger

MOTOR KRAFT 150 - 240 BHP.
MAX. INSTALLERT MOTOR VEKT 440 lbs. 200 kg.
MAX. TAKE-OFF VEKT (MTOW) 2,200 lbs. 998 kg.
DESIGN LOAD FACTOR (ultimate) @ 2,200 lbs. + 5.7, - 2.8
MAX. VINGE BESLASNING (@ 2,200 lbs.) 13.2 PSF 64.4 kg/m²
MAX. FART MED FLAP 80 MPH 129 km/h
MAX. CRUISE SPEED  -  VC 120 MPH 193 km/h
ABSOLUTT MAX FART (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.


JA 177
The JA177 Evolution has always been a unique ultralight (L.S.A.) since 2002, a well-done one of which will turn heads on any ramp or airfield in the word. Aerodynos of Colombia S.A. deliver the ultimate combination of performance, comfort, safety and efficiency.
Like a very high standard aircraft, every JA177 Evolution is built with exquisite attention to detail. From the cromoly 4130 steel cabin frame, 6061 T6 Aluminum to the custom metallic paint finish.



SPECIFICATIONS AND PERFORMANCE
Wing area 12 m2
Cord 1,45 m

Wingspan

7.80 m

Lenght

7.15 m

Height

2 m

Cabing width

1 m 12

Luggage compartment

1 m3 / 50 Lb

Empty weight as testet

275 kg

Max takeoff weight

475 kg

Ceiling

14.500 pies

Seats

2

Electric Propeller

Tri-blades IVO

Climb

5 m/s

Max cruise

80cv 210 km/h

VNE

240 km/h

Rotation Speed

20° flaps 50 km/h

Stalling Speed, flaps up and the flaps down

90 km/h- 20º de flaps 70 km/h

Maneuvepring speed, calculated

185 km/h

Fuel, usable

90 Lt (4.5 horas)
Takeoff runway 60 m (3000 pies)
Landing runway 90 m (alt 3000 pies)
Resistence, tested +4.5/-3 G

 

 

 

 

 

Seastar SP  /  Super Petrel

 


Rotax 912S
Cruise Speed (Km/h) 165
Max. Speed (Km/h) 175
V.NE. (Km/h) 180
Stall Speed (Km/h) 56
Climb Ratio (ft/min) 1000
Glide Ratio 10:01:00
Service Ceilling (ft) 10 000
Take Off (ground/water) (m) 80/120
Landing (ground/water) (m) 120/100
Fuel Capacity (L) 80
Endurance (hours) 05:00:00
.
WEIGHT
Empty Weight (kg) 315
Useful Load (kg)

185

Gross Weight (kg) 500 (540)
Load Factor (G) 4/ -2
.
DIMENSIONS
Lenght (m) 5,97
Height (m) 2,26
Wing Span (m) 8,9
Wing Surface (m²) 15
Seats 2
Landing Gear Trigear/Retractable



VIRUS UL Aircraft technical data
 
       

model

VIRUS 912 SW 80

VIRUS 912 SW 100

ENGINE ROTAX ROTAX 912 UL ROTAX 912 ULS
max power(with 2 carb.)

80 hp at 5800 rpm

100 hp at 5800 rpm
PROPELLER

Pipistrel VARIO

Variable pitch
SIZES  
 
wing span 10,71 m 10,71 m
length 6,5 m 6,5 m
height 1,85 1,85
wing area 9,51 m2 9,51 m2
rudder area 1,1 m2 1,1 m2
tail area 1,08 m2 1,08 m2
aspect ratio 11,3 11,3
positive flaps 9 deg,    19 deg  9 deg,    19 deg
negative flaps 5 deg  5 deg 
center of gravity 25% - 37% 25% - 37%
WEIGHTS  
 
empty weight

287 kg

289 kg
max take off weight (MTOW) 472.5 / 544 / 600 kg
 
472.5 / 544 / 600 kg
fuel tanks capacity 2 x 50 l 2 x 50 l
useful fuel 2 x 47 l 2 x 47 l
PERFORMANCES
DATA PUBLISHED FOR TOM 472.5 kg
stall with flaps 64 km/h 64 km/h
stall without flaps 79 km/h 79 km/h
cruising speed (75% power) 246 km/h 273 km/h
max. horizontal speed 264 km/h 283 km/h
VNE 302 km/h 302 km/h
max speed with airbrakes out 205 km/h 205 km/h
max speed with flaps down 130 km/h 130 km/h
turbulence penetration speed Vb
 
250 km/h 250 km/h
best climb speed 140 km/h 140 km/h
max climb rate (450 kg) 6,1 m/sec  8,4 m/sec
best glide ratio speed 118 km/h 118 km/h
best glide 1:17 1:15
take off run (450 kg) 140 m  95 m
take off over 15 m obstacle 225 m 175 m
service ceiling (450 kg) 6200 m  6800 m
45° - 45° roll time 1,6 sec  1,6 sec 
fuel consum. at cruis. speed 13,6 l/hour 17,8 l/hour
endurance 6,9 hours  5,3 hours
range distance 1650 km  1450 km 
max load factor permitted ( x 1,8) +4g  -2g  +4g  -2g 
design safety factors & tested minumum 1.875 minumum 1.875
VIRUS UL Aircraft technical data
 
       

model

VIRUS 912 SW 80

VIRUS 912 SW 100

ENGINE ROTAX ROTAX 912 UL ROTAX 912 ULS
max power(with 2 carb.)

80 hp at 5800 rpm

100 hp at 5800 rpm
PROPELLER

Pipistrel VARIO

Variable pitch
SIZES  
 
wing span 10,71 m 10,71 m
length 6,5 m 6,5 m
height 1,85 1,85
wing area 9,51 m2 9,51 m2
rudder area 1,1 m2 1,1 m2
tail area 1,08 m2 1,08 m2
aspect ratio 11,3 11,3
positive flaps 9 deg,    19 deg  9 deg,    19 deg
negative flaps 5 deg  5 deg 
center of gravity 25% - 37% 25% - 37%
WEIGHTS  
 
empty weight

287 kg

289 kg
max take off weight (MTOW) 472.5 / 544 / 600 kg
 
472.5 / 544 / 600 kg
fuel tanks capacity 2 x 50 l 2 x 50 l
useful fuel 2 x 47 l 2 x 47 l
PERFORMANCES
DATA PUBLISHED FOR TOM 472.5 kg
stall with flaps 64 km/h 64 km/h
stall without flaps 79 km/h 79 km/h
cruising speed (75% power) 246 km/h 273 km/h
max. horizontal speed 264 km/h 283 km/h
VNE 302 km/h 302 km/h
max speed with airbrakes out 205 km/h 205 km/h
max speed with flaps down 130 km/h 130 km/h
turbulence penetration speed Vb
 
250 km/h 250 km/h
best climb speed 140 km/h 140 km/h
max climb rate (450 kg) 6,1 m/sec  8,4 m/sec
best glide ratio speed 118 km/h 118 km/h
best glide 1:17 1:15
take off run (450 kg) 140 m  95 m
take off over 15 m obstacle 225 m 175 m
service ceiling (450 kg) 6200 m  6800 m
45° - 45° roll time 1,6 sec  1,6 sec 
fuel consum. at cruis. speed 13,6 l/hour 17,8 l/hour
endurance 6,9 hours  5,3 hours
range distance 1650 km  1450 km 
max load factor permitted ( x 1,8) +4g  -2g  +4g  -2g 
design safety factors & tested minumum 1.875 minumum 1.875

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