1st Flight 1991
The KAI KT-1 Woongbi is a Korean single-engine turboprop, basic training aircraft.
The KT-1 is the first completely indigenous Korean aircraft ever developed.
Variants
KTX-1 Yeo-Myung
Prototype primary trainer each with a different engine fitted, six built.
KTX-1 turboprop trainer in 1988, and the first prototype flew in 1991.
The first two prototypes were powered by the 550-shp. Pratt & Whitney Canada PT6A-25A turboprop.
KT-1
KT-1 is the basic trainer of the ROKAF.
Compared to the KTX-1 prototype, the KT-1 is bigger, heavier, the tail surfaces are relocated and it has a more powerful P&W Canada PT6A-62.(950-shp)
KA-1
An armed advanced trainer with light-attack and forward air control capabilities.
Several new features unique to the KA-1 are a head-up display and up-front control panel, MFD panels, and five hard points, two under each wing and one under the fuselage.
The hard points may be equipped with rocket launchers, gun pods or AIM-9 Sidewinder missiles.
KT-1B
Export version for Indonesia.
Main differences are in terms of avionics, some of which have been excluded or have had commercial off-the-shelf (COTS) alternatives used instead.
KT-1C
Improved, armed export version equipped with a centreline forward looking infrared pod.
The KT-1C can also be equipped with a 12.7 mm gun pod, chaffes, flares, training missiles, rockets or unguided bombs.
KT-1T
Export version for Turkey.
KT-1P
Export version for Peru.
KA-1P
Armed export version for Peru.
KA-1S
Armed export version for Senegal.
Specifications
Crew: 2
Length: 10.26 m (33 ft 8 in)
Wingspan: 10.59 m (34 ft 9 in)
Height: 3.68 m (12 ft 1 in)
Wing area: 16.01 m2 (172.3 sq ft)
Aspect ratio: 7
Airfoil: root: NACA 63-218; tip: NACA 63-212
Empty weight: 1,910 kg (4,211 lb)
Gross weight: 2,540 kg (5,600 lb)
Maximum fuel weight: 408 kg (899 lb)
Max takeoff weight: 3,311 kg (7,300 lb) (and Maximum Landing Weight)with external stores
3,205 kg (7,066 lb) training/utility
2,540 kg (5,600 lb) aerobatic
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
Powerplant: 1 × Pratt & Whitney Canada PT6A-62 turboprop engine, 708 kW (949 hp)
Propellers: 4-bladed Hartzell HC-E4N-2/E9512CB-1, 2.44 m (8 ft 0 in) diameter constant-speed fully feathering reversible propeller
Performance
Maximum speed: 518 km/h (322 mph, 280 kn) at 4,570 m (14,993 ft)
Maximum operating speed: 574 km/h (357 mph; 310 kn)
Stall speed: 132 km/h (82 mph, 71 kn) flaps down
Never exceed speed: 648 km/h (403 mph, 350 kn)
Range: 1,333 km (828 mi, 720 nmi) at 7,620 m (25,000 ft) with max internal fuel (30 minutes reserve)
Ferry range: 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)
Endurance: <4 hours at 6,100 m (20,013 ft) with max internal fuel (30 minutes reserve)
Service ceiling: 11,580 m (37,990 ft)
g limits: +7 -3.5 (aerobatic, clean)
+4.5 -2.3 (with external stores)
Rate of climb: 17.78 m/s (3,500 ft/min) at sea level, clean
Wing loading: 206.8 kg/m2 (42.4 lb/sq ft) with external stores
200.2 kg/m2 (41 lb/sq ft) training/utility
158.7 kg/m2 (33 lb/sq ft) aerobatic
Power/mass: 0.2137 kW/kg (0.1300 hp/lb)with external stores
0.221 kW/kg (0.134 hp/lb) training/utility
0.2785 kW/kg (0.1694 hp/lb) aerobatic
Armament
provision for practice bomb carriers on four under wing pylons
Avionics
VHF/UHF
IFF
Intercom
ELT optional
AHRS
TacAN
VOR/ILS optional.
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