Credit
Michal šenki · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
Empty; L-59E · includes gun
Single sourceMaximum take-off; L-59E · Max takeoff weight
Single source4,030 kg (8,885 lb) (includes gun)[source]
7,000 kg (15,432 lb)[source]
Empty; Gulfstream II-B · basic operating weight
Single sourceGross; Gulfstream II-B · Gross weight
Single sourceMaximum take-off; Gulfstream II-B · Max takeoff weight
Single source39,100 lb (17,735 kg) (basic operating weight)[source]
65,500 lb (29,710 kg)[source]
68,200 lb (30,935 kg)[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]
Gulfstream II-B · with 8 passengers, NBAA IFR reserves, crew of 3, 2,000 lb (900 kg) / pax
Single source3,550 nmi (4,090 mi, 6,570 km) with 8 passengers, NBAA IFR reserves, crew of 3, 2,000 lb (900 kg) / pax[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Configuration
| Specification | Aero L-59 Super Albatros | Grumman Gulfstream II |
|---|---|---|
| Type | Military trainer aircraft COIN[source] | Business jet[source] |
| Manufacturer | Aero Vodochody[source] | Grumman / Gulfstream Aerospace[source] |
| Status | Out of production, in service[source] | In service[source] |
| Primary users | Czech Air Force Egyptian Air Force Tunisian Air Force[source] | — |
| Number built | 80[source] | 256[source] |
| Manufactured | 1986–1996[source] | 1967–1980[source] |
| First flight | 30 September 1986[source] | 2 October 1966[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] | 28,300 lb (12,837 kg) maximum[source] |
| Stall speed | 185 km/h (115 mph, 100 kn) (flaps down)[source] | 105 kn (121 mph, 194 km/h) at MLW, 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 | — |
| National origin | — | United States[source] |
| Developed into | — | Gulfstream III[source] |
| Capacity | — | 19 (maximum certified) / 2,900 lb (1,315 kg) maximum payload[source] |
| Airfoil | — | stn.50: NACA 0012 modified ; stn 145: NACA 63A-009.5 ; stn 385: NACA 64 series modified[source] |
| Maximum zero-fuel weight | — | 42,000 lb (19,051 kg)[source] |
| Maximum landing weight | — | 58,500 lb (26,535 kg)[source] |
| Maximum cruising Mach number | — | M0.85 at max power at 30,000 ft (9,144 m) and AUW of 55,000 lb (24,948 kg)[source] |
| Maximum Mach speed | — | M0.85[source] |
| Economical cruise speed | — | M0.77[source] |
| Take-off run (FAA) | — | 5,850 ft (1,783 m)[source] |
| Landing run (FAA) | — | 3,400 ft (1,036 m)[source] |
| Operational Noise levels (FAR Pt.36) | — | Take-off: 91 EPNdB Approach: 97 EPNdB Sideline: 103 EPNdB[source] |
| Take-off | — | 91 EPNdB[source] |
| Approach | — | 97 EPNdB[source] |
| Sideline | — | 103 EPNdB[source] |