FORCETALLY
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At a glance
Measured figures
Tétras B · Length
Single source6.50 m (21 ft 4 in)[source]
KT-1 · Length
Single sourceConfiguration
| Specification | Humbert Tétras | KAI KT-1 Woongbi |
|---|---|---|
| Type | Two seat ultralight or kit build[source] | Basic trainer and light attack aircraft[source] |
| National origin | France[source] | South Korea[source] |
| Manufacturer | Humbert Aviation[source] | Korea Aerospace Industries[source] |
| Designer | Humbert Aviation[source] | Agency for Defence Development Korea Aerospace Industries |
10.3 m (33 ft 10 in)[source]
Empty; Tétras B · Empty weight
Single sourceMaximum take-off; Tétras B · Max takeoff weight
Single sourceMaximum take-off; Tétras B · where permitted
Single source256 kg (564 lb)[source]
450 kg (992 lb) ; where permitted, 495 kg (1,091 lb)[source]
Empty; KT-1 · Empty weight
Single sourceGross; KT-1 · Gross weight
Single sourceCruise; Tétras B · at 75% power and 3,048 m (10,000 ft)
Single sourceMaximum; Tétras B · Maximum speed
Single source194 km/h (121 mph, 105 kn)[source]
180 km/h (110 mph, 97 kn) at 75% power and 3,048 m (10,000 ft)[source]
Maximum; KT-1 · at 4,570 m (14,993 ft)
Single source644 km/h (400 mph, 348 kn) at 4,570 m (14,993 ft)[source]
Tétras B · with standard fuel capacity
Single source700 km (430 mi, 380 nmi) with standard fuel capacity[source]
Ferry; 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]
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]
KT-1 · Service ceiling
Single source11,580 m (37,990 ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Status | In production[source] | In service[source] |
|---|
| Number built | c.150 by 2010[source] | 186[source] |
|---|
| Manufactured | 1992-present[source] | 1999–present[source] |
|---|
| Introduction date | 1994[source] | 2000[source] |
|---|
| First flight | c.1992[source] | November 1991[source] |
|---|
| Capacity | — |
|---|
| Airfoil | NACA 23012[source] | root: NACA 63-218 ; tip: NACA 63-212[source] |
|---|
| Fuel capacity | 60 L (15.9 USgal, 13.2 Impgal) standard. Can be increased to 85 L (22.5 USgal, 18.7 Impgal) outside France.[source] | 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] |
|---|
| Propellers | 2-bladed DUC FC composite, 1.75 m (5 ft 9 in) diameter[source] | 4-bladed Hartzell HC-E4N-2/E9512CB-1, 2.44 m (8 ft 0 in) diameter constant-speed fully feathering reversible propeller[source] |
|---|
| Stall speed | 55 km/h (34 mph, 30 kn) flaps down[source] | 132 km/h (82 mph, 71 kn) flaps down[source] |
|---|
| g limits | +4/-2[source] | + 7 - 3.5 (aerobatic, clean)[source] |
|---|
| Primary users | — | Republic of Korea Air Force Indonesian Air Force Turkish Air Force Peruvian Air Force Senegalese Air Force[source] |
|---|
| Aspect ratio | — |
|---|
| Maximum fuel weight | — | 408 kg (899 lb)[source] |
|---|
| Never exceed speed | — | 648 km/h (403 mph, 350 kn)[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] |
|---|
Maximum take-off; KT-1 · (and Maximum Landing Weight)with external stores
Single source