Credit
US Air Force · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
T-41C · Length
Single source26 ft 11 in (8.20 m)[source]
M26 01 · Length
Single sourceConfiguration
| Specification | Cessna T-41 Mescalero | PZL M26 Iskierka |
|---|---|---|
| Type | Primary pilot trainer[source] | Trainer aircraft[source] |
| National origin | United States[source] | Poland[source] |
| Manufacturer | Cessna[source] | PZL Mielec[source] |
| Status | In service[source] | in production |
8.295 m (27 ft 3 in)[source]
T-41C · 1 × Continental IO-360-D Six-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Continental IO-360-D Six-cylinder air-cooled horizontally-opposed piston engine, 210 hp (160 kW)[source]
M26 01 · 1 × Textron Lycoming AEIO-540-L1B5 6-cylinder horizontally-opposed air-cooled piston engine
Single source1 × Textron Lycoming AEIO-540-L1B5 6-cylinder horizontally-opposed air-cooled piston engine, 224 kW (300 hp)[source]
T-41C · Service ceiling
Single source17,000 ft (5,200 m)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Primary users | United States Air Force United States Army Indonesian Air Force Turkish Air Force[source] | US civilian aviation Poland Venezuela[source] |
|---|
| Number built | T-41A : 230 T-41B : 255 T-41C : 52 T-41D : 299[source] |
|---|
| Manufactured | 1964–1996[source] | — |
|---|
| Introduction date | 1964[source] | — |
|---|
| Developed from | Cessna 172 Cessna R172[source] | — |
|---|
| Capacity | three passengers[source] | — |
|---|
| Propellers | 2-bladed variable-pitch propeller[source] | 3-bladed Hoffman HO-V123K-V/200AH-10 OR Hartzell HC-C3YR-4BF, 1.9 m (6 ft 3 in) diameter constant-speed propeller[source] |
|---|
| Alternative designation | T-41 Mescalero[source] | — |
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| First flight | — | July 15, 1986[source] |
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| Aspect ratio | — | 5.3[source] |
|---|
| Airfoil | — | NACA65 2 -415[source] |
|---|
| Fuel capacity | — | 369 L (97 US gal; 81 imp gal) in four wing tanks; Oil capacity 18 L (4.8 US gal; 4.0 imp gal)[source] |
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| Never exceed speed | — | 395 km/h (245 mph, 213 kn) Aerobatic mission; 371 km/h (231 mph; 200 kn) Utility mission[source] |
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| g limits | — | +6 / -3 Aerobatic mission; +4.4 / -1.76 Utility mission at Max take-off weight[source] |
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| Wing loading | — | 93.9 kg/m 2 (19.2 lb/sq ft) Aerobatic mission; 100 kg/m 2 (20 lb/sq ft) Utility mission[source] |
|---|
| Power/mass | — | 5.88 kg/kW (9.66 lb/hp) Aerobatic mission; 6.26 kg/kW (10.29 lb/hp) Utility mission[source] |
|---|
| Reported operators | — |
|
|---|
Maximum take-off; M26 01 · Utility mission
Single source