Credit
Michal šenki · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
L-59E · Length
Single source12.20 m (40 ft 0 in)[source]
E-6B · Length
Single sourceConfiguration
| Specification | Aero L-59 Super Albatros | Boeing E-6 Mercury |
|---|---|---|
| Type | Military trainer aircraft COIN[source] | Airborne command and control[source] |
| Manufacturer | Aero Vodochody[source] | Boeing[source] |
| Status | Out of production, in service[source] | In service[source] |
| Primary users | Czech Air Force Egyptian Air Force Tunisian Air Force[source] |
150 ft 4 in (45.82 m)[source]
Maximum; L-59E · at 5,000 m (16,000 ft)
Single source865 km/h (537 mph, 467 kn) at 5,000 m (16,000 ft)[source]
E-6B · Combat range
Single source6,350 nmi (7,310 mi, 11,760 km)[source]
L-59E · 1 × Lotarev DV-2 turbofan thrust
Single source1 × Lotarev DV-2 turbofan , 21.57 kN (4,850 lbf) thrust[source]
L-59E · 5,510 ft/min
Single source28.0 m/s (5,510 ft/min)[source]
E-6B · maximum with multiple refuelings
Single sourceE-6B · on station at 1,000 nmi (1,200 mi; 1,900 km) unrefueled
Single sourceE-6B · with one refueling
Single sourceon station at 1,000 nmi (1,200 mi; 1,900 km) 10 hours 30 minutes unrefueled 28 hours 54 minutes with one refueling 72 hours maximum with multiple refuelings[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Number built | 80[source] | 16[source] |
|---|
| Manufactured | 1986–1996[source] | — |
|---|
| First flight | 30 September 1986[source] | 19 February 1987[source] |
|---|
| Developed from | Aero L-39 Albatros[source] | Boeing 707[source] |
|---|
| Variant | Aero L-159 ALCA[source] | — |
|---|
| Fuel capacity | 1,537 L (406 US gal; 338 imp gal) including tip tanks[source] | — |
|---|
| Stall speed | 185 km/h (115 mph, 100 kn) (flaps down)[source] | — |
|---|
| Guns | one GSh-23L cannon in under-fuselage pod[source] | — |
|---|
| Hardpoints | four underwing hardpoints with a capacity of inner hardpoints 500 kg (1,100 lb)capacity, outer hardpoints 250 kg (550 lb)[source] | — |
|---|
| Country of origin | Czechoslovakia[source]Inventory Origin column; table 1, row 26, cell 2; revision 1374778711; retrieved 2026-10-01 | Vereinigte Staaten[source]Country of design · Entwurfsland |
|---|
| Primary user | — | United States Navy[source] |
|---|
| Introduction date | — | August 1989[source] |
|---|
| Powerplant | — | 4 × CFM International CFM56-2A-2 turbofan engines[source] |
|---|
| Wing loading | — | 112.13 lb/sq ft (547.5 kg/m 2 )[source] |
|---|
| Thrust/weight | — | 0.281[source] |
|---|
| Critical field length | — | 6,700 ft (2,042 m)[source] |
|---|
| Max effort take-off run | — | 5,400 ft (1,646 m)[source] |
|---|
| Landing run at max landing weight | — | 2,600 ft (792 m)[source] |
|---|