Credit
Doo Ho Kim · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
KT-1 · Length
Single source10.3 m (33 ft 10 in)[source]
Length
Single sourceConfiguration
| Specification | KAI KT-1 Woongbi | Socata TB 30 Epsilon |
|---|---|---|
| Type | Basic trainer and light attack aircraft[source] | Light military trainer aircraft[source] |
| National origin | South Korea[source] | — |
| Manufacturer | Korea Aerospace Industries[source] | SOCATA ( Aérospatiale )[source] |
| Designer | Agency for Defence Development Korea Aerospace Industries[source] | — |
| Status | In service |
7.59 m (24 ft 11 in)[source]
Empty; KT-1 · Empty weight
Single sourceGross; KT-1 · Gross weight
Single sourceMaximum take-off; KT-1 · (and Maximum Landing Weight)with external stores
Single source1,910 kg (4,211 lb)[source]
2,540 kg (5,600 lb)[source]
3,311 kg (7,300 lb) (and Maximum Landing Weight)with external stores[source]
Empty; Empty weight
Single sourceMaximum take-off; Max takeoff weight
Single sourceFerry; KT-1 · at 6,100 m (20,013 ft) with max internal and external fuel (30 minutes reserve)
Single sourceKT-1 · at 7,620 m (25,000 ft) with max internal fuel (30 minutes reserve)
Single source1,333 km (828 mi, 720 nmi) at 7,620 m (25,000 ft) with max internal fuel (30 minutes reserve)[source]
2,070 km (1,290 mi, 1,120 nmi) at 6,100 m (20,013 ft) with max internal and external fuel (30 minutes reserve)[source]
Range
Single source1,300 km (810 mi, 700 nmi)[source]
KT-1 · 1 × Pratt & Whitney Canada PT6A-62 turboprop engine
Single source1 × Pratt & Whitney Canada PT6A-62 turboprop engine, 708.4 kW (950.0 hp)[source]
× Lycoming AEIO-540-L1B5D 6-cylinder air-cooled horizontally-opposed piston engine
Single source× Lycoming AEIO-540-L1B5D 6-cylinder air-cooled horizontally-opposed piston engine, 220 kW (300 hp)[source]
KT-1 · < at 6,100 m (20,013 ft) with max internal fuel (
Single sourceKT-1 · reserve
Single source<4 hours at 6,100 m (20,013 ft) with max internal fuel (30 minutes reserve)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Active service[source] |
| Primary users | Republic of Korea Air Force Indonesian Air Force Turkish Air Force Peruvian Air Force Senegalese Air Force[source] | French Air Force (historical) Portuguese Air Force Togolese Air Force Senegalese Air Force[source] |
|---|
| Number built | 186[source] | — |
|---|
| Manufactured | 1999–present[source] | 1979-1989[source] |
|---|
| Introduction date | 2000[source] | 1983[source] |
|---|
| First flight | November 1991[source] | 22 December 1979[source] |
|---|
| Fuel capacity | 551 L (146 US gal; 121 imp gal) in two wing tanks with provision for two 189 L (50 US gal; 42 imp gal) drop-tanks on the inboard pylons[source] | — |
|---|
| Aspect ratio |
|---|
| Airfoil | root: NACA 63-218 ; tip: NACA 63-212[source] | root: RA 1643 (16%); tip: RA 1243 (12%)[source] |
|---|
| Maximum fuel weight | 408 kg (899 lb)[source] | — |
|---|
| Propellers | 4-bladed Hartzell HC-E4N-2/E9512CB-1, 2.44 m (8 ft 0 in) diameter constant-speed fully feathering reversible propeller[source] | 2-bladed constant-speed propeller[source] |
|---|
| Stall speed | 132 km/h (82 mph, 71 kn) flaps down[source] | 115 km/h (71 mph, 62 kn)[source] |
|---|
| Never exceed speed | 648 km/h (403 mph, 350 kn)[source] | 520 km/h (320 mph, 280 kn)[source] |
|---|
| g limits | + 7 - 3.5 (aerobatic, clean)[source] | — |
|---|
| Wing loading | 206.8 kg/m 2 (42.4 lb/sq ft) with external stores[source] | — |
|---|
| Power/mass | 0.2137 kW/kg (0.1300 hp/lb)with external stores[source] | — |
|---|
| Hardpoints | — | Up to 480 kg (1,100 lbs) on four underwing hardpoints (export versions)[source] |
|---|