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]
DHC-5D · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | De Havilland Canada DHC-5 Buffalo |
|---|---|---|
| Type | Light aircraft[source] | Utility aircraft[source] |
| Manufacturer | Cirrus Aircraft[source] | de Havilland Canada[source] |
| Number built | 2,084 (through 2025)[source] | 122[source] |
| Manufactured | 1999–present[source] | 1965–1972, 1974–1986 |
79 ft 0 in (24.08 m)[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]
DHC-5D · 2 × General Electric CT64-820-4 turboprop engines, 3,133 shp ( ) each
Single source2 × General Electric CT64-820-4 turboprop engines, 3,133 shp (2,336 kW) each[source]
DHC-5D · Wing area
Single source945 sq ft (87.8 m 2 )[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] | 9 April 1964[source] |
|---|
| Developed into | Cirrus SR22[source] | — |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 41 troops or 24 stretchers or 18,000 lb (8,200 kg) payload[source] |
|---|
| Propellers | 3-bladed[source] | 3-bladed Hamilton Standard 63E60-25, 14 ft 6 in (4.42 m) diameter fully-feathering reversible-pitch propellers[source] |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | 73 kn (84 mph, 135 km/h) 40 degree flaps at 46,900 lb (21,273 kg)[source] |
|---|
| National origin | United States[source] | — |
|---|
| Status | — | In limited service[source] |
|---|
| Primary user | — | Royal Canadian Air Force (historical)[source] |
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| Introduction date | — | 1965[source] |
|---|
| Developed from | — | De Havilland Canada DHC-4 Caribou[source] |
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| Aspect ratio | — | 9.75:1[source] |
|---|
| Airfoil | — | root: NACA 64 3 A417.5 (mod); tip: NACA 63 2 A615[source] |
|---|
| Fuel capacity | — | 1,755 imp gal (2,108 US gal; 7,980 L)[source] |
|---|
| g limits | — | 2.5g (manoeuvring limit load)[source] |
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| Take-off run | — | 2,300 ft (701 m)[source] |
|---|
| Take-off distance to 50 ft (15 m) | — | 2,750 ft (838 m) (mid cg range)[source] |
|---|
| Landing run | — | 850 ft (259 m)[source] |
|---|
| Landing distance from 50 ft (15 m) | — | 2,010 ft (613 m)[source] |
|---|
| Country of origin | — | Canada[source]Inventory Origin column; table 1, row 11, cell 2; revision 1376550040; retrieved 2026-09-30 |
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