Credit
Tomás Del Coro from Las Vegas, Nevada, USA · CC BY-SA 2.0 · Resized · CC BY-SA 2.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
SR20-G3 · Length
Single source26 ft 0 in (7.92 m)[source]
1124A Westwind II · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | IAI Westwind |
|---|---|---|
| Type | Light aircraft[source] | Business jet[source] |
| Manufacturer | Cirrus Aircraft[source] | Aero Commander Israel Aircraft Industries[source] |
| Number built | 2,084 (through 2025)[source] | 442[source] |
| Manufactured | 1999–present[source] | 1965–1987[source] |
15.93 m (52 ft 3 in)[source]
1124A Westwind II · 10 pax
Single source1124A Westwind II · with maximum fuel and four passengers
Single source4,430 km (2,750 mi, 2,390 nmi) 10 pax, 5,385 km (3,346 mi; 2,908 nmi) with maximum fuel and four passengers[source]
SR20-G3 · 1 × Continental IO-360-ES six cylinder, horizontally-opposed piston aircraft engine
Single source1 × Continental IO-360-ES six cylinder, horizontally-opposed piston aircraft engine , 200 hp (150 kW)[source]
1124A Westwind II · 2 × Honeywell TFE731-3-1G turbofan engines thrust each
Single source2 × Honeywell TFE731-3-1G turbofan engines, 16.46 kN (3,700 lbf) thrust each[source]
1124A Westwind II · Wing area
Single source28.64 m 2 (308.3 sq ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| First flight | 21 March 1995[source] | 27 January 1963[source] |
|---|
| Developed into | Cirrus SR22[source] | IAI Astra Gulfstream G100[source] |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 7 pax normal (maximum 10) / 1,474 kg (3,250 lb) maximum payload[source] |
|---|
| Propellers | 3-bladed[source] | — |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | 184 km/h (114 mph, 99 kn) at maximum landing weight, flaps down, engines idling[source] |
|---|
| National origin | United States[source] | — |
|---|
| Status | — | Limited service[source] |
|---|
| Primary user | — | Pel-Air[source] |
|---|
| Introduction date | — | 1965[source] |
|---|
| Developed from | — | Aero Commander 500[source] |
|---|
| Fuel capacity | — | 4,345 kg (9,579 lb)[source] |
|---|
| Aspect ratio | — | 6.51[source] |
|---|
| Airfoil | — | IAI 54-12 (Sigma 1 modified)[source] |
|---|
| Never exceed speed | — | 868 km/h (539 mph, 469 kn) at 8,840 m (29,000 ft)[source] |
|---|
| Wing loading | — | 372 kg/m 2 (76 lb/sq ft)[source] |
|---|
| Thrust/weight | — | 0.31[source] |
|---|
| Take-off balanced field length | — | 1,600 m (5,200 ft)[source] |
|---|
| Landing run from 15 m (49 ft) | — | 747 m (2,450 ft) at maximum landing weight[source] |
|---|
| Country of origin | — | United States[source]Original Aero Commander 1121 design |
|---|