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 | IAR 99 |
|---|---|---|
| Type | Basic trainer[source] | Advanced trainer and light attack aircraft[source] |
| Manufacturer | Grob Aircraft[source] | Avioane Craiova[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] | — |
| Manufactured |
11.01 m (36 ft 1 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]
Maximum; trainer, clean
Single source865 km/h (537 mph, 467 kn) trainer, clean[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]
Range
Single sourceTrainer with internal fuel; Ground attack with internal fuel
Single source1,100 km (680 mi, 590 nmi) Trainer with internal fuel; Ground attack with internal fuel 967 km (601 mi; 522 nmi)[source]
hi-lo-hi at 5,280 kg (11,640 lb)all-up weight
Single source345 km (214 mi, 186 nmi) hi-lo-hi at 5,280 kg (11,640 lb)all-up weight[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]
1 × Turbomecanica / Rolls-Royce Viper Mk632-41M turbojet thrust
Single source1 × Turbomecanica / Rolls-Royce Viper Mk632-41M turbojet, 17.79 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.
1985–present[source]
1985–2008[source] |
| Introduction date | 1999[source] | 1987[source] |
|---|
| First flight | November 1985[source] | 21 December 1985[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | Internal:1,370 L (360 US gal; 300 imp gal); External:up to 450 L (120 US gal; 99 imp gal) (in 225 L (59 US gal; 49 imp gal) drop tanks)[source] |
|---|
| Aspect ratio | 8.2:1[source] | 5.2[source] |
|---|
| Airfoil | Eppler 696[source] | NACA 64 1 A-214 (modified)[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] | — |
|---|
| Never exceed speed | 341 km/h (212 mph, 184 kn)[source] | — |
|---|
| g limits | + 6.0/ - 3.0[source] | +7 / -3.6[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | Romania[source] |
|---|
| Primary user | — | Romanian Air Force[source] |
|---|
| Number built | — | 28 (25 Șoim/C 3 prototip)[source] |
|---|
| Wing loading | — | 235.2 kg/m 2 (48.2 lb/sq ft) Trainer; 297.2 kg/m 2 (60.9 lb/sq ft) Ground attack[source] |
|---|
| Guns | — | 1 × 23 mm Gryazev-Shipunov GSh-23L autocannon[source] |
|---|
| Hardpoints | — | 4 underwing hardpoints capable of holding 250 kg each and 1 central hardpoint capable of holding 400 kg with a capacity of up to 450 kg (990 lb) of stores (the underwing hardpoints are wet capable of carrying 225l drop tanks)[source] |
|---|
Maximum take-off; Trainer
Single source