Credit
Alan Wilson from Peterborough, Cambs, UK · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
1976 150M Commuter II · Length
Single source23 ft 11 in (7.29 m)[source]
KT-1 · Length
Single sourceConfiguration
| Specification | Cessna 150 | KAI KT-1 Woongbi |
|---|---|---|
| Type | Light utility aircraft, basic trainer[source] | Basic trainer and light attack aircraft[source] |
| Manufacturer | Cessna[source] | Korea Aerospace Industries[source] |
| Status | In service[source] | In service[source] |
| Number built | 23,839[source] | 186[source] |
10.3 m (33 ft 10 in)[source]
Cruise; 1976 150M Commuter II · at 10,000 ft (3,050 m) (econ cruise)
Single sourceMaximum; 1976 150M Commuter II · at sea level
Single source109 kn (125 mph, 202 km/h) at sea level[source]
82 kn (94 mph, 152 km/h) at 10,000 ft (3,050 m) (econ cruise)[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]
1976 150M Commuter II · econ cruise, standard fuel
Single source420 nmi (480 mi, 780 km) (econ cruise, standard fuel)[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]
1976 150M Commuter II · 1 × Continental O-200-A air-cooled horizontally-opposed engine
Single source1 × Continental O-200-A air-cooled horizontally-opposed engine, 100 hp (75 kW)[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]
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.
| Manufactured | 1958–1977[source] | 1999–present[source] |
|---|
| First flight | September 12, 1957[source] | November 1991[source] |
|---|
| Variant | Cessna 152[source] | — |
|---|
| Capacity | one passenger (plus two children not exceeding 120 lb (54 kg) on optional bench seat in baggage space)[source] | — |
|---|
| Fuel capacity | 22.5 US gal (18.7 imp gal; 85 L) usable internal fuel[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] |
|---|
| Aspect ratio | 6.7:1[source] |
|---|
| Airfoil | NACA 2412[source] | root: NACA 63-218 ; tip: NACA 63-212[source] |
|---|
| Propellers | 2-bladed McCauley 1A102/OCM metal fixed-pitch propeller, 5 ft 9 in (1.75 m) 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 | 42 kn (48 mph, 78 km/h) (flaps down, power off)[source] | 132 km/h (82 mph, 71 kn) flaps down[source] |
|---|
| Never exceed speed | 140 kn (160 mph, 260 km/h)[source] | 648 km/h (403 mph, 350 kn)[source] |
|---|
| Take-off run to 50 ft (15 m) | 1,385 ft (422 m)[source] | — |
|---|
| Landing run from 50 ft (15 m) | 1,075 ft (328 m)[source] | — |
|---|
| Country of origin | United States[source] | — |
|---|
| National origin | — | South Korea[source] |
|---|
| Designer | — | Agency for Defence Development Korea Aerospace Industries[source] |
|---|
| Primary users | — | Republic of Korea Air Force Indonesian Air Force Turkish Air Force Peruvian Air Force Senegalese Air Force[source] |
|---|
| Introduction date | — | 2000[source] |
|---|
| Maximum fuel weight | — | 408 kg (899 lb)[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] |
|---|
Maximum take-off; KT-1 · (and Maximum Landing Weight)with external stores
Single source