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]
G-4M · Length
Single sourceConfiguration
| Specification | Grob G 115 | Soko G-4 Super Galeb |
|---|---|---|
| Type | Basic trainer[source] | Military trainer aircraft[source] |
| Manufacturer | Grob Aircraft[source] | SOKO[source] |
| Status | active[source] | In service[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | Serbian Air Force Myanmar Air Force Montenegrin Air Force (historical) Yugoslav Air Force (historical) |
12.25 m (40 ft 2 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; G-4M · at 6,000m
Single sourceMaximum; G-4M · clean at 6,000 m (13,000 ft)
Single sourceG 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-4M · Combat range
Single sourceG-4M · with cannon pack and four BL755 cluster bombs (combat radius
Single source1,300 km (810 mi, 700 nmi) with cannon pack and four BL755 cluster bombs (combat radius 485 km)[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-4M · 1 × Rolls-Royce Viper 632-46 turbojet thrust
Single source1 × Rolls-Royce Viper 632-46 turbojet , 17.8 kN (4,000 lbf) thrust[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Manufactured | 1985–present[source] | 1984–1991[source] |
|---|
| Introduction date | 1999[source] | 1983[source] |
|---|
| First flight | November 1985[source] | 17 July 1978[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 1,882 kg (maximum internal and external fuel)[source] |
|---|
| Aspect ratio | 8.2:1[source] | 5.01[source] |
|---|
| Airfoil | Eppler 696[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] | 180 km/h (97 mph, 112 kn) (flaps and undercarriage down)[source] |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | 921 km/h (572 mph, 497 kn) 0.9M at 11,000 m[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | -4.2 to +8[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | Yugoslavia[source] |
|---|
| Designer | — | Aeronautical Technical Institute[source] |
|---|
| Number built | — | 85[source] |
|---|
| Time to altitude | — | 6 minutes to 8,000m[source] |
|---|
Maximum take-off; G-4M · Max takeoff weight
Single source