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]
M26 01 · Length
Single sourceConfiguration
| Specification | Grob G 115 | PZL M26 Iskierka |
|---|---|---|
| Type | Basic trainer[source] | Trainer aircraft[source] |
| Manufacturer | Grob Aircraft[source] | PZL Mielec[source] |
| Status | active[source] | in production[source] |
| Primary users | Royal Air Force Egyptian Air Force Finnish Air Force Royal Navy Army Air Corps (UK)[source] | US civilian aviation Poland Venezuela |
8.295 m (27 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]
Maximum; M26 01 · Aerobatic mission
Single sourceMaximum; M26 01 · Utility mission
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]
M26 01 · 1 × Textron Lycoming AEIO-540-L1B5 6-cylinder horizontally-opposed air-cooled piston engine
Single source1 × Textron Lycoming AEIO-540-L1B5 6-cylinder horizontally-opposed air-cooled piston engine, 224 kW (300 hp)[source]
G 115E · Service ceiling
Single source6,095 m (20,000 ft)[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] | July 15, 1986[source] |
|---|
| Fuel capacity | 143 L (31 imp gal; 38 US gal) usable[source] | 369 L (97 US gal; 81 imp gal) in four wing tanks; Oil capacity 18 L (4.8 US gal; 4.0 imp gal)[source] |
|---|
| Aspect ratio | 8.2:1[source] | 5.3[source] |
|---|
| Airfoil | Eppler 696[source] | NACA65 2 -415[source] |
|---|
| Propellers | 3-bladed Hoffmann HO-V343K-V/183GY Constant-speed propeller , 1.83 m (6 ft 0 in) diameter[source] | 3-bladed Hoffman HO-V123K-V/200AH-10 OR Hartzell HC-C3YR-4BF, 1.9 m (6 ft 3 in) diameter constant-speed propeller[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] | 395 km/h (245 mph, 213 kn) Aerobatic mission; 371 km/h (231 mph; 200 kn) Utility mission[source] |
|---|
| g limits | + 6.0/ - 3.0[source] | +6 / -3 Aerobatic mission; +4.4 / -1.76 Utility mission at Max take-off weight[source] |
|---|
| Country of origin | Deutschland[source]Country of design · Entwurfsland | — |
|---|
| Number built | — |
|---|
| Wing loading | — | 93.9 kg/m 2 (19.2 lb/sq ft) Aerobatic mission; 100 kg/m 2 (20 lb/sq ft) Utility mission[source] |
|---|
| Power/mass | — | 5.88 kg/kW (9.66 lb/hp) Aerobatic mission; 6.26 kg/kW (10.29 lb/hp) Utility mission[source] |
|---|
| National origin | — | Poland[source] |
|---|
| Reported operators | — |
|
|---|
Maximum take-off; M26 01 · Utility mission
Single source1,040 kg (2,293 lb)[source]
1,315 kg (2,899 lb) Aerobatic mission; 1,400 kg (3,100 lb) Utility mission[source]
330 km/h (210 mph, 180 kn) Aerobatic mission; 321 km/h (199 mph; 173 kn) Utility mission[source]