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]
Y-12 (II · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | Harbin Y-12 |
|---|---|---|
| Type | Light aircraft[source] | Twin-engine turboprop utility aircraft[source] |
| Manufacturer | Cirrus Aircraft[source] | Harbin Aircraft Industry Group[source] |
| Number built | 2,084 (through 2025)[source] | 300+[source] |
| Manufactured | 1999–present[source] | 1985–present[source] |
14.86 m (48 ft 9 in)[source]
Cruise; SR20-G3 · TAS
Single source155 kn (178 mph, 287 km/h) TAS[source]
Cruise; Y-12 (II · (max) at 3,000 m (9,800 ft)
Single sourceMaximum; Y-12 (II · V MO (maximum operating speed) at 3,000 m (9,800 ft)
Single source328 km/h (204 mph, 177 kn) V MO (maximum operating speed) at 3,000 m (9,800 ft)[source]
292 km/h (181 mph, 158 kn) (max) at 3,000 m (9,800 ft)[source]
Y-12 (II · at econ cruise, 45 min reserves at 3,000 m (9,800 ft)
Single source1,340 km (830 mi, 720 nmi) at econ cruise, 45 min reserves at 3,000 m (9,800 ft)[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]
Y-12 (II · 2 × Pratt & Whitney Canada PT6A-27 turboprop engines each
Single source2 × Pratt & Whitney Canada PT6A-27 turboprop engines, 462 kW (620 hp) each[source]
Y-12 (II · Wing area
Single source34.27 m 2 (368.9 sq ft)[source]
Y-12 (II · at econ cruise
Single source5 hours 12 minutes at econ cruise[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] | 14 July 1982[source] |
|---|
| Developed into | Cirrus SR22[source] | — |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 17 max / 1,700 kg (3,748 lb) max payload[source] |
|---|
| Propellers | 3-bladed[source] | 3-bladed Hartzell HC-B3TN-3B/T10173B-3, 2.49 m (8 ft 2 in) diameter constant-speed fully-feathering reversible-pitch propellers (4 and 5 bladed propellers used on some models)[source] |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | — |
|---|
| National origin | United States[source] | China[source] |
|---|
| Status | — | In service, in production[source] |
|---|
| Primary users | — | People's Liberation Army Air Force Myanmar Air Force Iran Revolutionary Guard Air Force Zambian Air Force[source] |
|---|
| Developed from | — | Harbin Y-11[source] |
|---|
| Fuel capacity | — | 1,616 L (427 US gal; 355 imp gal) / 1,230 kg (2,712 lb) max usable fuel weight[source] |
|---|
| Airfoil | — | LS(1)-0417[source] |
|---|
| Wing loading | — | 145.9 kg/m 2 (29.9 lb/sq ft)[source] |
|---|
| Power/mass | — | 0.106 kW/kg (0.064 hp/lb)[source] |
|---|
| Take-off run | — | 370 m (1,210 ft)[source] |
|---|
| Take-off run to 15 m (49 ft) | — | 490 m (1,610 ft)[source] |
|---|
| Landing run | — | 340 m (1,120 ft)[source] |
|---|
| Landing run from 15 m (49 ft) | — | 630 m (2,070 ft)[source] |
|---|