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At a glance
Measured figures
An-28 · Length
Single source13.10 m (43 ft 0 in)[source]
SR20-G3 · Length
Single sourceConfiguration
| Specification | Antonov An-28 | Cirrus SR20 |
|---|---|---|
| Type | Short-range airliner , utility aircraft[source] | Light aircraft[source] |
| Designer | Antonov[source] | — |
| Built by | WSK PZL Mielec[source] | — |
| Status | In service[source] | — |
| Primary user | Aeroflot (former)[source] | — |
| Number built |
26 ft 0 in (7.92 m)[source]
Cruise; An-28 · at 3,000 m (9,800 ft)
Single sourceMaximum; An-28 · at 3,000 m (9,800 ft)
Single source350 km/h (220 mph, 190 kn) at 3,000 m (9,800 ft)[source]
335 km/h (208 mph, 181 kn) at 3,000 m (9,800 ft)[source]
Cruise; SR20-G3 · TAS
Single source155 kn (178 mph, 287 km/h) TAS[source]
An-28 · (max fuel, 1,000 kg (2,200 lb) payload)
Single source1,365 km (848 mi, 737 nmi) (max fuel, 1,000 kg (2,200 lb) payload)[source]
An-28 · 2 × Glushenkov TVD-10B turboprop engines (960 shp) each
Single source2 × Glushenkov TVD-10B turboprop engines, 720 kW (960 shp) each[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]
An-28 · Wing area
Single source39.72 m 2 (427.5 sq ft)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
191[source] |
2,084 (through 2025)[source] |
| Manufactured | 1975–1993[source] | 1999–present[source] |
|---|
| Introduction date | 1986[source] | — |
|---|
| First flight | September 1969[source] | 21 March 1995[source] |
|---|
| Developed from | Antonov An-14[source] | — |
|---|
| Variant | PZL M28 Skytruck[source] | — |
|---|
| Developed into | Antonov An-38[source] | Cirrus SR22[source] |
|---|
| Capacity | 17 passengers or 1,750 kg (3,860 lb)[source] | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] |
|---|
| Aspect ratio | 12.3[source] | — |
|---|
| Airfoil | TsAGI R-II-14 (14% thickness)[source] | — |
|---|
| Fuel capacity | 1,960 L (430 imp gal; 520 US gal)[source] | — |
|---|
| Propellers | 3-bladed AW-24AN, 2.80 m (9 ft 2 in) diameter[source] | 3-bladed[source] |
|---|
| Never exceed speed | 390 km/h (240 mph, 210 kn)[source] | — |
|---|
| g limits | +3[source] | — |
|---|
| Take-off run to 10.7 m (35 ft) | 410 m (1,350 ft)[source] | — |
|---|
| Landing run from 15 m (50 ft) | 315 m (1,033 ft)[source] | — |
|---|
| Manufacturer | — | Cirrus Aircraft[source] |
|---|
| Stall speed | — | 56 kn (64 mph, 104 km/h) CAS[source] |
|---|
| National origin | — | United States[source] |
|---|