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]
Universal · Length
Single sourceConfiguration
| Specification | Grob G 115 | Neiva Universal |
|---|---|---|
| Type | Basic trainer[source] | Basic trainer and ground attack aircraft[source] |
| Manufacturer | Grob Aircraft[source] | Neiva[source] |
| Status | active[source] | — |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | Brazilian Air Force Chilean Air Force[source] |
8.60 m (28 ft 3 in)[source]
Cruise; G 115E · long range cruising speed
Single sourceMaximum; G 115E · Maximum speed
Single source250 km/h (160 mph, 130 kn)[source]
178 km/h (111 mph, 96 kn) (long range cruising speed)[source]
Cruise; Universal · at sea level (max. cruise, 75% power)
Single sourceMaximum; Universal · at sea level
Single sourceG 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]
Universal · 1 × Lycoming IO-540 -K1D5 six-cylinder horizontally-opposed air-cooled piston engine
Single source1 × Lycoming IO-540 -K1D5 six-cylinder horizontally-opposed air-cooled piston engine , 220 kW (300 hp)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured |
|---|
1985–present[source] |
| — |
| Introduction date | 1999[source] | — |
|---|
| First flight | November 1985[source] | 29 April 1966[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 332 L (88 US gal; 73 imp gal)[source] |
|---|
| Aspect ratio | 8.2:1[source] | 7.1:1[source] |
|---|
| Airfoil | Eppler 696[source] | NACA 63 2 A315 at root, NACA 63 1 212 at tip[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | 2-bladed Hartzell HC-C2YK-4/C8475-A2 non-feathering constant speed propeller , 2.13 m (7 ft 0 in) diameter[source] |
|---|
| Stall speed | 91 km/h (57 mph, 49 kn) (60 degree flap)[source] | 104 km/h (65 mph, 56 kn) (flaps down)[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 500 km/h (310 mph, 270 kn)[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | — |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | Brazil[source] |
|---|
| Number built | — | 189[source] |
|---|
| Guns | — | 7.62 mm machine gun pods on hardpoints[source] |
|---|
| Hardpoints | — |
|---|
| Takeoff run to 15 m (50 ft) | — | 510 m (1,670 ft)[source] |
|---|
| Landing run from 15 m (50 ft) | — | 600 m (1,969 ft)[source] |
|---|