Aircraft Name MTOW EMPTY WEIGHT FUEL WEIGHT

Gippsland GA8 4000 lb (1814 kg) 2198 lbs (997 kg)

CHEROKEE SIX 300 3400 lb (1542 kg) 1788 lb (811 kg) 700 lb (317 kg)
Cessna 210 Centurion3400 lb (1542 kg) 1960 lb (889 kg)
Neiva EMB-202 Ipane 3,417 lb (1,550 kg) 2,249 lb (1,020 kg)643.7498 lb (292 kg)
ROBIN R 2120 ALPHA1764 lb (800 kg) 1,199 lb (544 kg) 191.4 lb (87 kg)

Aircraft Name WING AREA WF/WO W/P

Gippsland GA8 Airvan 214 ft²(19.9 m²)
CHEROKEE SIX 300 174.5 ft² (16.22 m²) 0.206
Cessna 210 Centurion175 ft² (16.25 m²)
Neiva EMB-202 Ipane 214.6 ft² (19.94 m²) 3,417 lb (1,550 kg)1,653 lb (750 kg)
ROBIN R 2120 ALPHA134.5 ft² (12.50 m²) 0.1085 14.24 lb/HP

Aircraft Name PROPELLER DIAMETE SFC(lb/hp-hr) L/D

Gippsland GA8 Airvan 84 inches (2134 mm)
CHEROKEE SIX 300 80 in (2023 mm)
Cessna 210 Centurion90 in (2286 mm)
Neiva EMB-202 Ipane 84 in (2130 mm)
ROBIN R 2120 ALPHA72 in (1830 mm) 0.48 13.45

Aircraft Name Vstall Range Endurance

Gippsland GA8 Airvan 60 mph (97 km/h) 749 mi.(1,206 km) 6 hours
CHEROKEE SIX 300 63 mph (101km/hr) 1041 mi (1675 km) 6.5 hr
Cessna 210 Centurion63 mph (101 km/h) 1225 mi (1972 km)
Neiva EMB-202 Ipane 64 mph (103 km/hr) 583 mi (938 km0
ROBIN R 2120 ALPHA55 mph (89 km/hr) 586 mi (944 km) 5.87 hrs
 WE/WO

0.526

98 lb (292 kg)
0.68

W/S MAX ENGINE RATING (BHP)

300 BHP
19.5 300 BHP

15.92 lb/ ft² (77.7 kg/m²)

13.11 lb/ft^2 118 BHP

Vmax
161 mph (259 km/h)
174 mph (280 km/hr)

160 mph ( 257 kph)

Takeoff Run

700 ft (213 m)
800 ft (244 m)
1090 ft (332 m)
1610 ft (490 m)
Airplane No: 1

A. Weight
A.1 Gross Weight (MTOW)
A.2 Useful Load
Crew
Passengers
Baggage
Fuel Load
Oil Load
Total
A.3 Empty Weight = (MTOW-Useful Load)

B. Dimensions (External)
B.1 Wing Span
B.2 Wing Chord at Root (CR)
B.3 Wing Chord at Tip (CT)
B.4 Wing Aspect Ration (AR)
B.5 Length (Overall)
B.6 Height (Overall)
B.7 Tail Plane Span
B.8 Wheel Track
B.9 Wheel Base
B.10 Propeller Diameter
B.11 Propeller Ground Clearance
B.12 Cabin Door Height
Width

C. Areas
C.1 Wing Area (Sref OR Sw)
C.2 Aileron Area
C.3 Flaps Area
C.4 Vertical Stabilizer Area
C.5 Rudder Area
C.6 Horizontal Stabilizer Area
C.7 Elevator

D. Loadings
D.1 Wing Loading (W/S)
 D.2 Power Loading (HP/W)

E. Engine Specifications
E.1 Rated Maximum Horespower
E.2 Rated Maximum RPM
E.3 Specific Fuel Consumption
E.4 Number of Cylinder
E.5 Engine Dry Weight
E.6 Engine Dimensions
Width
Height

F. Performance
F.1 Top Speed, Vmax
F.2 Cruising Speed, Vcruise
F.3 Stalling Speed, Vstall Flaps
Flaps Down
F.4 Maximum Rate of Climb at S.L.
F.5 Service Ceiling
F.6 Takeoff Run
F.7 Landing Run
F.8 Endurance
F.9 Range
Aircraft Model: Gippsland GA8

SI UNIT IMPERIAL UNIT

1814 kg 4000 lb
845 kg 1862.5 lbs
159 kg 350 lbs
388 kg 855 lbs
51 kg 113 lbs
237 kg 522 lbs
10 kg 22.5 lbs
845 kg 1862.5 lbs
969 kg 2,137.5 lb

12.412 m 488.68 in
1.6 m 63 in
1.6m 63 in
8:1 8:1
8.949 m 352.3 in
3.885 m 153 in
4.166 m 164 in
2.794 m 110 in
2.299 m 90.5 in
2.134 m 84 in
12 in
64 kts
57 kts
Airplane No: 2

A. Weight
A.1 Gross Weight (MTOW)
A.2 Useful Load
Crew
Passengers
Baggage
Fuel Load
Oil Load
Total
A.3 Empty Weight = (MTOW-Useful Load)

B. Dimensions (External)
B.1 Wing Span
B.2 Wing Chord at Root (CR)
B.3 Wing Chord at Tip (CT)
B.4 Wing Aspect Ration (AR)
B.5 Length (Overall)
B.6 Height (Overall)
B.7 Tail Plane Span
B.8 Wheel Track
B.9 Wheel Base
B.10 Propeller Diameter
B.11 Propeller Ground Clearance
B.12 Cabin Door Height
Width

C. Areas
C.1 Wing Area (Sref OR Sw)
C.2 Aileron Area
C.3 Flaps Area
C.4 Vertical Stabilizer Area
C.5 Rudder Area
C.6 Horizontal Stabilizer Area
C.7 Elevator

D. Loadings
D.1 Wing Loading (W/S)
 D.2 Power Loading (HP/W)

E. Engine Specifications
E.1 Rated Maximum Horespower
E.2 Rated Maximum RPM
E.3 Specific Fuel Consumption
E.4 Number of Cylinder
E.5 Engine Dry Weight
E.6 Engine Dimensions
Width
Height

F. Performance
F.1 Top Speed, Vmax
F.2 Cruising SPeed, Vcruise
F.3 Stalling Speed, Vstall Flaps
Flaps Down
F.4 Maximum Rate of Climb at S.L.
F.5 Service Ceiling
F.6 Takeoff Run
F.7 Landing Run
F.8 Endurance
F.9 Range
Aircraft Model: CHEROKEE SIX 300

SI UNIT IMPERIAL UNIT

1542 kg 3400 lb
729 kg 1607 lb
159 kg 350 lb
490 kg 1080 lb
64 kg 140 lb
317 kg 700 lb
10.21 kg 22.5 lb
3311.21 kg 7299.5 lb
1793 lb

117.241 m 32 ft 8 in
Airplane No: 3

A. Weight
A.1 Gross Weight (MTOW)
A.2 Useful Load
Crew
Passengers
Baggage
Fuel Load
Oil Load
Total
A.3 Empty Weight = (MTOW-Useful Load)

B. Dimensions (External)
B.1 Wing Span
B.2 Wing Chord at Root (CR)
B.3 Wing Chord at Tip (CT)
B.4 Wing Aspect Ration (AR)
B.5 Length (Overall)
B.6 Height (Overall)
B.7 Tail Plane Span
B.8 Wheel Track
B.9 Wheel Base
B.10 Propeller Diameter
B.11 Propeller Ground Clearance
B.12 Cabin Door Height
Width

C. Areas
C.1 Wing Area (Sref OR Sw)
C.2 Aileron Area
C.3 Flaps Area
C.4 Vertical Stabilizer Area
C.5 Rudder Area
C.6 Horizontal Stabilizer Area
C.7 Elevator

D. Loadings
D.1 Wing Loading (W/S)
 D.2 Power Loading (HP/W)

E. Engine Specifications
E.1 Rated Maximum Horespower
E.2 Rated Maximum RPM
E.3 Specific Fuel Consumption
E.4 Number of Cylinder
E.5 Engine Dry Weight
E.6 Engine Dimensions
Width
Height

F. Performance
F.1 Top Speed, Vmax
F.2 Cruising SPeed, Vcruise
F.3 Stalling Speed, Vstall Flaps
Flaps Down
F.4 Maximum Rate of Climb at S.L.
F.5 Service Ceiling
F.6 Takeoff Run
F.7 Landing Run
F.8 Endurance
F.9 Range
Aircraft Model: Cessna 210 Centurion

SI UNIT IMPERIAL UNIT

Airplane No: 4

A. Weight
A.1 Gross Weight (MTOW)
A.2 Useful Load
Crew
Passengers
Baggage
Fuel Load
Oil Load
Total
A.3 Empty Weight = (MTOW-Useful Load)

B. Dimensions (External)
B.1 Wing Span
B.2 Wing Chord at Root (CR)
B.3 Wing Chord at Tip (CT)
B.4 Wing Aspect Ration (AR)
B.5 Length (Overall)
B.6 Height (Overall)
B.7 Tail Plane Span
B.8 Wheel Track
B.9 Wheel Base
B.10 Propeller Diameter
B.11 Propeller Ground Clearance
B.12 Cabin Door Height
Width

C. Areas
C.1 Wing Area (Sref OR Sw)
C.2 Aileron Area
C.3 Flaps Area
C.4 Vertical Stabilizer Area
C.5 Rudder Area
C.6 Horizontal Stabilizer Area
C.7 Elevator

D. Loadings
D.1 Wing Loading (W/S)
 D.2 Power Loading (HP/W)

E. Engine Specifications
E.1 Rated Maximum Horespower
E.2 Rated Maximum RPM
E.3 Specific Fuel Consumption
E.4 Number of Cylinder
E.5 Engine Dry Weight
E.6 Engine Dimensions
Width
Height

F. Performance
F.1 Top Speed, Vmax
F.2 Cruising SPeed, Vcruise
F.3 Stalling Speed, Vstall Flaps
Flaps Down
F.4 Maximum Rate of Climb at S.L.
F.5 Service Ceiling
F.6 Takeoff Run
F.7 Landing Run
F.8 Endurance
F.9 Range
Aircraft Model: Neiva EMB-202 Ipanema

SI UNIT IMPERIAL UNIT

1,550 kg 3,417 lb
565 kg 1,245.61 lb
1
0
750 kg 1,650 lb
87 kg 191.4 lb
12 kg 26.46 lb

544 kg 1,199 lb

11.69 m 460.25 in
1.71 m 67.5 in
1.71 m 67.5 in
6.9 6.9
7.43 m 292.5197 in
2.20 m 86.6142 in
3.66 m 144.0945 in
2.20 m 86.6142 in
5.20 m 204.724 in
2.13 m 83.8583 in
N/A
N/A
N/A

19.94 sq m 214.6 sq ft
1.60 sq m 17.22 sq ft
2.30 sq m 24.76 sq ft
0.58 sq m 6.24 sq ft
0.63 sq m 6.78 sq ft
3.17 sq m 34.12 sq ft
1.50 sq m 16.15 sq ft

77.7 kg/ sq m 15.92 lb/ sq ft

6.92 kg/ kW 11.39 lb/ hp

Textron Lycoming IO-540-K1J5D

223.71 kw 300 hp
2,700 rpm

6
214.096 kg 472 lb
0.94 m 37.19
0.85 m 33.38 in
0.62 m 24.56 in

272 km/h 169 mph

213 km/h 132 mph
103 km/h 64 mph
92 km/h 57 mph
283 m/ min 930 ft/min
3,740 m 11,380 ft
200 m 655 ft
153 m 505 ft

506 km 583 m
Airplane No: 5

A. Weight
A.1 Gross Weight (MTOW)
A.2 Useful Load
Crew
Passengers
Baggage
Fuel Load
Oil Load
Total
A.3 Empty Weight = (MTOW-Useful Load)

B. Dimensions (External)
B.1 Wing Span
B.2 Wing Chord at Root (CR)
B.3 Wing Chord at Tip (CT)
B.4 Wing Aspect Ration (AR)
B.5 Length (Overall)
B.6 Height (Overall)
B.7 Tail Plane Span
B.8 Wheel Track
B.9 Wheel Base
B.10 Propeller Diameter
B.11 Propeller Ground Clearance
B.12 Cabin Door Height
Width

C. Areas
C.1 Wing Area (Sref OR Sw)
C.2 Aileron Area
C.3 Flaps Area
C.4 Vertical Stabilizer Area
C.5 Rudder Area
C.6 Horizontal Stabilizer Area
C.7 Elevator

D. Loadings
D.1 Wing Loading (W/S)
 D.2 Power Loading (HP/W)

E. Engine Specifications
E.1 Rated Maximum Horespower
E.2 Rated Maximum RPM
E.3 Specific Fuel Consumption
E.4 Number of Cylinder
E.5 Engine Dry Weight
E.6 Engine Dimensions
Width
Height

F. Performance
F.1 Top Speed, Vmax
F.2 Cruising SPeed, Vcruise
F.3 Stalling Speed, Vstall Flaps
Flaps Down
F.4 Maximum Rate of Climb at S.L.
F.5 Service Ceiling
F.6 Takeoff Run
F.7 Landing Run
F.8 Endurance
F.9 Range
Aircraft Model: ROBIN R 2120 ALPHA

SI UNIT IMPERIAL UNIT

800 kg 1764 lb
256 kg 565 lb
77.11 kg 170 lb
77.11 kg 170 lb
10.38 22.84 lb
87 kg 191.4 lb
4.4 kg 10.76 lb

544 kg 1199 lb

8.33 m 27.33 ft.

1.56 m 5.12 ft.
1.56 m 5.12 ft.
5.55
6.64 m 21.78 ft.
2.13 6.99 ft.
3.04 m 9.97 ft.
2.65 m 8.69 ft.
1.43 m 4.69 ft.
1.83 m 6 ft.
0.22 m 0.72 ft.
0.74 m 2.44 ft
1.09 m 3.57 ft

12.50 sq m 134.5 sq ft
1.06 sq m 11.41 sq ft
1.34 sq m 14.42 sq ft
0.31 sq m 3.32 sq ft
0.59 sq m 6.32 sq ft
0.99 sq m 10.69 sq ft
0.99 sq m 10.69 sq ft

64 kg/ sq m 13.11 lb/ sq ft

 9.09 kg/kW 14.94 lb/HP

Lycoming O-235-L-2A
87.99 kW 118 HP
2800 rpm
0.29 kg/kW/hr 0.48 lb/hp/hr
4 cyl.
252 kg 555.57 lb.
0.57 m 1.86 ft
0.81 m 2.67 ft
0.76 m 2.5 ft

257 km/hr 159.79 mph

193 km/hr 120 mph
105.56 km/hr 65.59 mph
88.89 km/hr 55.24 mph
192 m/min 630 ft/min
4572 m 15,000 ft.
490 m 1610 ft.
480 m 1575 ft.
5.87 hrs
944 km 586 mi.