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
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]
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]
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]
Ferry; PC-7 · Ferry range
Single sourcePC-7 · standard range without external drop tanks, ferry range with external drop tanks, (cruise power, at 5,000 m (16,000 ft) - 20 min reserves)
Single source1,200 km (750 mi, 650 nmi) standard range without external drop tanks, ferry range with external drop tanks, (cruise power, at 5,000 m (16,000 ft) - 20 min reserves)[source]
2,630 km (1,630 mi, 1,420 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]
PC-7 · 1 × Pratt & Whitney Canada PT6A -25A turboprop derated from
Single sourcePC-7 · 650 shp
Single source1 × Pratt & Whitney Canada PT6A -25A turboprop , 410 kW (550 hp)(derated from 485 kW (650 shp))[source]
KT-1 · (3,500 ft/min) at sea level, clean
Single source17.78 m/s (3,500 ft/min) at sea level, clean[source]
PC-7 · (2,150 ft/min) climb to 5,000 m in 9 min 0 sec take-off run 780 m at max take-off weight, landing run 505 m at max landing weight
Single source10.9 m/s (2,150 ft/min) climb to 5,000 m in 9 min 0 sec take-off run 780 m at max take-off weight, landing run 505 m at max landing weight[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Configuration
| Specification | KAI KT-1 Woongbi | Pilatus PC-7 |
|---|---|---|
| Type | Basic trainer and light attack aircraft[source] | Trainer aircraft[source] |
| National origin | South Korea[source] | — |
| Manufacturer | Korea Aerospace Industries[source] | Pilatus Aircraft[source] |
| Designer | Agency for Defence Development Korea Aerospace Industries[source] | — |
| Status | In service[source] | In service[source] |
| Primary users | Republic of Korea Air Force Indonesian Air Force Turkish Air Force Peruvian Air Force Senegalese Air Force[source] | Mexican Air Force Indian Air Force South African Air Force Royal Malaysian Air Force[source] |
| Number built | 186[source] | >618[source] |
| Manufactured | 1999–present[source] | 1966–present[source] |
| Introduction date | 2000[source] | PC-7 : 1978 PC-7 Mk.II M : 1994 PC-7 MKX : 2021[source] |
| First flight | November 1991[source] | PC-7 : 12 April 1966 ( 1966-04-12 ) (prototype) 18 August 1978 ( 1978-08-18 ) (production) PC-7 Mk.II M : 28 September 1992 ( 1992-09-28 )[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] | 474 L (104 imp gal; 125 US gal) usable internal fuel, 2x 240 L (53 imp gal; 63 US gal) external fuel drop tanks • Max landing weight: 2,565 kg[source] |
| Aspect ratio | 6.5:1[source] | |
| Airfoil | root: NACA 63-218 ; tip: NACA 63-212[source] | NACA 64 2 A-415 at root, 64 1 A-612 at tip[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] | 3-bladed Hartzell HC-B3TN-2 / T10173C-8 constant-speed propeller , 2.36 m (7 ft 9 in) diameter[source] |
| Stall speed | 132 km/h (82 mph, 71 kn) flaps down[source] | 119 km/h (74 mph, 64 kn) (flaps and gear down, power off)[source] |
| Never exceed speed | 648 km/h (403 mph, 350 kn)[source] | 500 km/h (310 mph, 270 kn) EAS[source] |
| g limits | + 7 - 3.5 (aerobatic, clean)[source] | -3 / +6[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] | — |
| Developed from | — | Pilatus P-3[source] |
| Developed into | — | Pilatus PC-9[source] |
| Capacity | — | two[source] |
| Hardpoints | — | 6 × underwing hardpoints for bombs and rockets with a capacity of 1,040 kg (2,294 lb)[source] |
| Alternative designation | — | Pilatus PC-7 Turbo Trainer[source] |
| Country of origin | — | Switzerland[source] |