Credit
Alan Wilson from Peterborough, Cambs, UK · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
1976 150M Commuter II · Length
Single source23 ft 11 in (7.29 m)[source]
G 115E · Length
Single sourceConfiguration
| Specification | Cessna 150 | Grob G 115 |
|---|---|---|
| Type | Light utility aircraft, basic trainer[source] | Basic trainer[source] |
| Manufacturer | Cessna[source] | Grob Aircraft[source] |
| Status | In service[source] | active[source] |
| Number built | 23,839[source] | — |
| Manufactured | 1958–1977 |
7.79 m (25 ft 7 in)[source]
Empty; 1976 150M Commuter II · Empty weight
Single sourceMaximum take-off; 1976 150M Commuter II · Max takeoff weight
Single source1,122 lb (509 kg)[source]
1,600 lb (726 kg)[source]
Empty; G 115E · Empty weight
Single sourceMaximum take-off; G 115E · Max takeoff weight
Single sourceCruise; 1976 150M Commuter II · at 10,000 ft (3,050 m) (econ cruise)
Single sourceMaximum; 1976 150M Commuter II · at sea level
Single source109 kn (125 mph, 202 km/h) at sea level[source]
82 kn (94 mph, 152 km/h) at 10,000 ft (3,050 m) (econ cruise)[source]
Cruise; G 115E · long range cruising speed
Single sourceMaximum; G 115E · Maximum speed
Single source1976 150M Commuter II · 1 × Continental O-200-A air-cooled horizontally-opposed engine
Single source1 × Continental O-200-A air-cooled horizontally-opposed engine, 100 hp (75 kW)[source]
G 115E · 1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Lycoming AEIO-360-B1F/B 4-cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
1985–present[source] |
| First flight | September 12, 1957[source] | November 1985[source] |
|---|
| Variant | Cessna 152[source] | — |
|---|
| Capacity | one passenger (plus two children not exceeding 120 lb (54 kg) on optional bench seat in baggage space)[source] | — |
|---|
| Fuel capacity | 22.5 US gal (18.7 imp gal; 85 L) usable internal fuel[source] | 143 L (31 imp gal; 38 US gal) usable[source] |
|---|
| Aspect ratio | 6.7:1[source] | 8.2:1[source] |
|---|
| Airfoil | NACA 2412[source] | Eppler 696[source] |
|---|
| Propellers | 2-bladed McCauley 1A102/OCM metal fixed-pitch propeller, 5 ft 9 in (1.75 m) diameter[source] | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] |
|---|
| Stall speed | 42 kn (48 mph, 78 km/h) (flaps down, power off)[source] | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] |
|---|
| Never exceed speed | 140 kn (160 mph, 260 km/h)[source] | 341 km/h (212 mph, 184 kn)[source] |
|---|
| Take-off run to 50 ft (15 m) | 1,385 ft (422 m)[source] | — |
|---|
| Landing run from 50 ft (15 m) | 1,075 ft (328 m)[source] | — |
|---|
| Country of origin | United States[source] | Deutschland[source]Country of design · Entwurfsland |
|---|
| Primary users | — | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] |
|---|
| Introduction date | — | 1999[source] |
|---|
| g limits | — | + 6.0/ - 3.0[source] |
|---|