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]
M18B Dromader · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | PZL-Mielec M-18 Dromader |
|---|---|---|
| Type | Light aircraft[source] | Utility aircraft[source] |
| Manufacturer | Cirrus Aircraft[source] | PZL-Mielec[source] |
| Number built | 2,084 (through 2025)[source] | 759+[source] |
| Manufactured | 1999–present[source] | 1976-present |
9.47 m (31 ft 1 in)[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]
M18B Dromader · 1 × PZL Kalisz ASz-621R 9-cylinder air-cooled radial piston engine
Single source1 × PZL Kalisz ASz-621R 9-cylinder air-cooled radial piston engine, 731 kW (980 hp)[source]
M18B Dromader · Wing area
Single source40 m 2 (430 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 August 1976[source] |
|---|
| Developed into | Cirrus SR22[source] | PZL-Mielec M-21 Dromader Mini PZL-Mielec M-24 Dromader Super PZL-Mielec M-25 Dromader Mikro[source] |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 2,500 L (660 US gal; 550 imp gal) liquid or 2,200 kg (4,900 lb) dry chemical in fibreglass hopper forward of the cockpit (smaller hopper in M18BS)[source] |
|---|
| Propellers | 3-bladed[source] | 4-bladed PZL Warszawa AW-2-30, 3.3 m (10 ft 10 in) diameter constant speed aluminium alloy propeller[source] |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | 108 km/h (67 mph, 58 kn) flaps down[source] |
|---|
| National origin | United States[source] | Poland[source] |
|---|
| Status | — | Active, in production[source] |
|---|
| Developed from | — | Rockwell Thrush Commander[source] |
|---|
| Fuel capacity | — | 510 kg (1,120 lb) max fuel weight[source] |
|---|
| Aspect ratio | — | 7.8[source] |
|---|
| Airfoil | — | root: NACA 4416 ; tip: NACA 4412 outer wing panels[source] |
|---|
| Never exceed speed | — | 280 km/h (170 mph, 150 kn)[source] |
|---|
| g limits | — | +3.4 / -1.4[source] |
|---|
| Wing loading | — | 105 kg/m 2 (22 lb/sq ft)[source] |
|---|
| Power/mass | — | 5.75 kg/kW (11.92 lb/hp)[source] |
|---|