Credit
Alan Wilson · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
G 115E · Length
Single source7.79 m (25 ft 7 in)[source]
Length
Single sourceConfiguration
| Specification | Grob G 115 | Schweizer SGS 2-33 |
|---|---|---|
| Type | Basic trainer[source] | Training sailplane[source]SGS 2-33 |
| Manufacturer | Grob Aircraft[source] | Schweizer Aircraft Corporation[source]SGS 2-33 |
| Status | active[source] | Production completed[source]SGS 2-33 |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] |
25 ft 9 in (7.85 m)[source]
G 115E · 45% power at FL 80, 45 min reserves
Single source1,150 km (710 mi, 620 nmi) (45% power at FL 80, 45 min reserves)[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]
G 115E · Service ceiling
Single source6,095 m (20,000 ft)[source]
G 115E · 1,050 ft/min
Single source5.3 m/s (1,050 ft/min)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Manufactured | 1985–present[source] | 1967-1981[source]SGS 2-33 |
|---|
| Introduction date | 1999[source] | — |
|---|
| First flight | November 1985[source] | 1965[source]SGS 2-33 |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | — |
|---|
| Aspect ratio | 8.2:1[source] | 11.85:1[source] |
|---|
| Airfoil | Eppler 696[source] | NACA 43012A[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | — |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 36 mph (57 km/h, 31 kn) dual[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 98 mph (157 km/h, 85 kn) in smooth air, rough air and aero-tow[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | +4.67 -2.56[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | United States[source]SGS 2-33 |
|---|
| Designer | — | Ernest Schweizer[source]SGS 2-33 |
|---|
| Primary user | — | Royal Canadian Air Cadets[source]SGS 2-33 |
|---|
| Number built | — | 579[source]SGS 2-33 |
|---|
| Developed from | — | Schweizer 2-22[source]SGS 2-33 |
|---|
| Capacity | — | one passenger[source] |
|---|
| Max winch-launch speed | — | 60 kn (110 km/h; 69 mph)[source] |
|---|
| Maximum glide ratio | — | 22.25:1[source] |
|---|
| Best glide speed dual | — | 45 kn (83 km/h; 52 mph)[source] |
|---|
| Rate of sink | — | 187 ft/min (0.95 m/s) dual[source] |
|---|
| Minimum sink speed | — | 37 kn (69 km/h; 43 mph)[source] |
|---|
| Wing loading | — | 4.74 lb/sq ft (23.14 kg/m 2 ) max[source] |
|---|