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]
An-70 · Length
Single sourceConfiguration
| Specification | Aero L-59 Super Albatros | Antonov An-70 |
|---|---|---|
| Type | Military trainer aircraft COIN[source] | Military transport aircraft[source] |
| Manufacturer | Aero Vodochody[source] | Kyiv Aircraft Production Plant[source] |
| Status | Out of production, in service[source] | Completed state tests, open for production[source] |
| Primary users | Czech Air Force Egyptian Air Force Tunisian Air Force[source] |
40.73 m (133 ft 8 in)[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]
L-59E · at 7,000 m (23,000 ft) (with maximum internal and external fuel)
Single source2,000 km (1,200 mi, 1,100 nmi) at 7,000 m (23,000 ft) (with maximum internal and external fuel)[source]
An-70 · runway
Single sourceAn-70 · with 47,000 kg (103,617 lb) payload from
Single source1,350 km (840 mi, 730 nmi) with 47,000 kg (103,617 lb) payload from 1,800 m (5,900 ft) runway[source]
An-70 · 4 × Progress D-27 propfan each
Single source4 × Progress D-27 propfan , 10,350 kW (13,880 hp) each[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 · Wing area
Single source18.80 m 2 (202.4 sq ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Number built | 80[source] | 2 prototypes[source] |
|---|
| Manufactured | 1986–1996[source] | 1991–1996 2012–2015[source] |
|---|
| First flight | 30 September 1986[source] | 16 December 1994[source] |
|---|
| Developed from | Aero L-39 Albatros[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] | 113 km/h (70 mph, 61 kn)[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 | — |
|---|
| National origin | — | Soviet Union Ukraine[source] |
|---|
| Designer | — | Antonov Design Bureau[source] |
|---|
| Built by | — | Antonov Serial Production Plant[source] |
|---|
| Primary user | — | Ukrainian Air Force[source] |
|---|
| Capacity | — | 300 troops or 206 stretcher cases / 47,000 kg (103,617 lb) max payload[source] |
|---|
| Airfoil | — | TsAGI P-202[source] |
|---|
| Propellers | — | 14-bladed Aerosyla Stupino SV-27, 4.5 m (14 ft 9 in) diameter contra-rotating propeller (8-bladed forward; 6-bladed rear)[source] |
|---|
| Power/mass | — | 0.316 kW/kg (0.192 hp/lb) max[source] |
|---|
| Take-off field length | — | 1,800 m (5,900 ft)[source] |
|---|
| Landing field length | — | 2,000 m (6,600 ft)[source] |
|---|
| Take-off run STOL 30,000 kg (66,139 lb) payload | — | 600 m (2,000 ft)[source] |
|---|
| Take-off run STOL 35,000 kg (77,162 lb) payload | — | 915 m (3,000 ft)[source] |
|---|