Credit
Gennady Misko · CC BY-SA 3.0 · Resized · CC BY-SA 3.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
An-24V · Length
Single source23.53 m (77 ft 2 in)[source]
SR20-G3 · Length
Single sourceConfiguration
| Specification | Antonov An-24 | Cirrus SR20 |
|---|---|---|
| Type | Regional airliner / military transport[source] | Light aircraft[source] |
| National origin | Soviet Union[source] | United States[source] |
| Manufacturer | Antonov Serial Production Plant Irkutsk Aviation Plant Ulan-Ude Aviation Plant[source] | Cirrus Aircraft[source] |
| Designer | Antonov[source] | — |
26 ft 0 in (7.92 m)[source]
Cruise; An-24V · at 6,000 m (20,000 ft)
Single sourceMaximum; An-24V · at 6,000 m (20,000 ft)
Single source485 km/h (301 mph, 262 kn) at 6,000 m (20,000 ft)[source]
450 km/h (280 mph, 240 kn) at 6,000 m (20,000 ft)[source]
Cruise; SR20-G3 · TAS
Single source155 kn (178 mph, 287 km/h) TAS[source]
An-24V · with maximum fuel
Single sourceAn-24V · with maximum payload
Single source2,400 km (1,500 mi, 1,300 nmi) with maximum fuel; 550 km (340 mi; 300 nmi) with maximum payload[source]
An-24V · 2 × Ivchenko AI-24 A turboprop engines (2,550 shp) each (eshp)
Single source2 × Ivchenko AI-24 A turboprop engines, 1,900 kW (2,550 shp) each (eshp)[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-24V · Wing area
Single source74.98 m 2 (807.1 sq ft)[source]
SR20-G3 · 828 ft/min (
Single source828 ft/min (4.21 m/s)[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Status | In service[source] | — |
|---|
| Primary users | Aeroflot (former) IrAero Utair Polar Airlines[source] | — |
|---|
| Number built | >1,367[source] | 2,084 (through 2025)[source] |
|---|
| Manufactured | 1959–1976[source] | 1999–present[source] |
|---|
| Introduction date | 1962[source] | — |
|---|
| First flight | 29 October 1959[source] | 21 March 1995[source] |
|---|
| Developed into | Antonov An-30 Antonov An-26 Antonov An-32 Xi'an Y-7 Antonov/Taqnia An-132[source] | Cirrus SR22[source] |
|---|
| Capacity | 50 passengers[source] | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] |
|---|
| Aspect ratio | 11.7:1[source] | — |
|---|
| Fuel capacity | 5,550 L (1,470 US gal; 1,220 imp gal)[source] | — |
|---|
| Propellers | 4-bladed AV-72 constant-speed propellers , 3.90 m (12 ft 10 in) diameter[source] | 3-bladed[source] |
|---|
| Time to altitude | 17.5 min to 6,000 m (20,000 ft) 45.2 min to 8,100 m (26,600 ft)[source] | — |
|---|
| Role | 50-seat twin turboprop regional airliner[source] | — |
|---|
| Source measurement | The Antonov An-24 ( Russian / Ukrainian : Антонов Ан-24 ; NATO reporting name : Coke ) is a 50-seat twin turboprop regional airliner designed in 1957 in the Soviet Union by the Antonov Design Bureau . Later variants saw other uses, such as military transport and aerial cartography . The aircraft was manufactured by the Kyiv, Irkutsk and Ulan-Ude Aviation Factories. It was license-produced in China as the early versions of the Xi'an Y-7 .[source]Antonov An-24 · Lead; only the objects and conditions stated in this passage 200 were built (9 in 1962, 191 in 1963) of this improved version, delivered directly from the Kiev factory. It seated 44 passengers and had a larger interior volume. In addition, the APU exhaust was moved to the tip of the starboard nacelle. This was the second time the designation was used.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage 400 aircraft were built in the second production version. A passenger version with seating for up to 52. Maximum takeoff weight was increased to 21 tonnes, a window was added on each side, the double slotted flaps were replaced with single slotted flaps, and the centre chord was extended to compensate for the poor performance of the flaps. Some aircraft were delivered with four additional fuel bladders in the centre wing. Production began in 1964.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage Turbojet boosted export version, similar to the An-24V but fitted with a 1,985-lb (8830 N) thrust auxiliary turbojet engine in the starboard nacelle.[source]Antonov An-24 · Variants / Produced aircraft; only the objects and conditions stated in this passage An-24PS ( Poiskovo-Spasahtel'nyy – SAR)[source]Antonov An-24 · Variants / Special mission aircraft; only the objects and conditions stated in this passage Capacity: 50 passengers[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Length: 23.53 m (77 ft 2 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Wingspan: 29.20 m (95 ft 10 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Height: 8.32 m (27 ft 4 in)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Wing area: 74.98 m 2 (807.1 sq ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Empty weight: 13,300 kg (29,321 lb)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Max takeoff weight: 21,000 kg (46,297 lb)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Powerplant: 2 × Ivchenko AI-24 A turboprop engines, 1,900 kW (2,550 shp) each (eshp)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Propellers: 4-bladed AV-72 constant-speed propellers , 3.90 m (12 ft 10 in) diameter[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Maximum speed: 485 km/h (301 mph, 262 kn) at 6,000 m (20,000 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Cruise speed: 450 km/h (280 mph, 240 kn) at 6,000 m (20,000 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Range: 2,400 km (1,500 mi, 1,300 nmi) with maximum fuel; 550 km (340 mi; 300 nmi) with maximum payload[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Service ceiling: 8,400 m (27,600 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage Time to altitude: 17.5 min to 6,000 m (20,000 ft) 45.2 min to 8,100 m (26,600 ft)[source]Antonov An-24 · Specifications (An-24V); only the objects and conditions stated in this passage | — |
|---|
| Stall speed | — | 56 kn (64 mph, 104 km/h) CAS[source] |
|---|