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BoomerTheDoomer · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
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At a glance
Measured figures
L-39C · Length
Single sourceL-39C · Only the source-declared variant L-39C · L-39C
Single sourceConfiguration
| Specification | L-39C | Grob G 120TP |
|---|---|---|
| Variant description | L-39C (C for Cvičná – training)[source]Only the source-declared variant L-39C Standard basic trainer for Soviet Union, Czechoslovakia and export. Originally designated L-39, but renamed L-39C when later variants appeared. Two pylons under wing. Approximately 2,260 built.[source]Only the source-declared variant L-39C | — |
| Airfoil | NACA 64A012 modified[source]Only the source-declared variant L-39C | — |
| Never exceed speed | 980 km/h (610 mph, 530 kn) / M0.8[source]Only the source-declared variant L-39C | — |
| Time to altitude | 5,000 m (16,000 ft) in 5 minutes[source] |
12.13 m (39 ft 10 in)[source]Only the source-declared variant L-39C
39.8 ft[source]L-39C · Aero Vodochody L-39C (x2)
Length
Single source8.4 m (27 ft 7 in)[source]
Empty; L-39C · Only the source-declared variant L-39C · L-39C
Single sourceMaximum take-off; L-39C · Max takeoff weight
Single sourceMaximum take-off; L-39C · Only the source-declared variant L-39C · L-39C
Single source3,455 kg (7,617 lb)[source]Only the source-declared variant L-39C
4,700 kg (10,362 lb)[source]Only the source-declared variant L-39C
10,360 lbs[source]L-39C · Aero Vodochody L-39C (x2)
Empty; Empty weight
Single sourceMaximum take-off; Max takeoff weight
Single sourceMaximum; L-39C · Only the source-declared variant L-39C · L-39C · at 5,000 m (16,000 ft)
Single source750 km/h (470 mph, 400 kn) at 5,000 m (16,000 ft)[source]Only the source-declared variant L-39C
Ferry; L-39C · Only the source-declared variant L-39C · L-39C · internal and external fuel
Single sourceL-39C · Only the source-declared variant L-39C · L-39C · internal fuel
Single source1,100 km (680 mi, 590 nmi)(internal fuel)[source]Only the source-declared variant L-39C
1,750 km (1,090 mi, 940 nmi) (internal and external fuel)[source]Only the source-declared variant L-39C
991 nm[source]L-39C · Aero Vodochody L-39C (x2)
at 5,000 ft and 75% power
Single sourceFerry; at 10,000 ft and 45% power
Single source1 × Rolls-Royce M250-B17F Turboprop aircraft engine
Single source1 × Rolls-Royce M250-B17F Turboprop aircraft engine , 340 kW (456 hp)[source]
L-39C · Only the source-declared variant L-39C · L-39C · 1 × Ivchenko AI-25TL turbofan engine thrust
Single source1 × Ivchenko AI-25TL turbofan engine, 16.87 kN (3,790 lbf) thrust[source]Only the source-declared variant L-39C
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| — |
| Wing loading | 250 kg/m 2 (51 lb/sq ft)[source]Only the source-declared variant L-39C | — |
|---|
| Thrust/weight | 0.37[source]Only the source-declared variant L-39C | — |
|---|
| Take-off roll | 530 m (1,740 ft)[source]Only the source-declared variant L-39C | — |
|---|
| Landing roll | 650 m (2,130 ft)[source]Only the source-declared variant L-39C | — |
|---|
| Hardpoints | Up to 284 kg (626 lb) of stores on two external hardpoints[source]Only the source-declared variant L-39C | — |
|---|
| Manufacturer | Aero Vodochody[source]L-39C · Aero Vodochody L-39C (x2) | Grob Aircraft[source] |
|---|
| Country of origin | Czechoslovakia[source]L-39C · Aero Vodochody L-39C (x2) | — |
|---|
| Engine | Ivchenko AI-25TL[source]L-39C · Aero Vodochody L-39C (x2) | — |
|---|
| Thurst (mil) | 3,800 lbs[source]L-39C · Aero Vodochody L-39C (x2) | — |
|---|
| Vne | 530 kts[source]L-39C · Aero Vodochody L-39C (x2) | — |
|---|
| Climb Rate (Sea Level) | 4,100 fpm[source]L-39C · Aero Vodochody L-39C (x2) | — |
|---|
| Type | — | Trainer[source] |
|---|
| National origin | — | Germany[source] |
|---|
| Status | — | In production[source] |
|---|
| Primary users | — | Indonesian Air Force Mexican Air Force Bangladesh Air Force UK Military Flying Training System Swedish Air Force[source] |
|---|
| Manufactured | — | 2010-present[source] |
|---|
| Introduction date | — | 2013[source] |
|---|
| First flight | — | 2010[source] |
|---|
| Developed from | — | Grob G 120[source] |
|---|
| Fuel capacity | — | 360 litres (79 imp gal; 95 US gal)[source] |
|---|
| Propellers | — | 5-bladed MT Propeller , 2.1 m (6 ft 11 in) diameter[source] |
|---|
| Stall speed | — | 107 km/h (67 mph, 58 kn) (MSL, landing configuration)[source] |
|---|
| g limits | — | +6/-4G[source] |
|---|