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]
Tu-134A · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | Tupolev Tu-134 |
|---|---|---|
| Type | Light aircraft[source] | Airliner[source] |
| Manufacturer | Cirrus Aircraft[source] | Tupolev, KhAZ[source] |
| Number built | 2,084 (through 2025)[source] | 854 (852 + 2 prototypes)[source] |
| Manufactured | 1999–present[source] | 1966–1989[source] |
37.1 m (121 ft 9 in)[source]
Tu-134A · fuselage diameter
Single source2.9 m (9 ft 6 in) fuselage diameter[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]
Tu-134A · 2 × Soloviev D-30-II turbofan engines thrust each
Single source2 × Soloviev D-30-II turbofan engines, 66.68 kN (14,990 lbf) thrust each[source]
SR20-G3 · 828 ft/min (
Single source828 ft/min (4.21 m/s)[source]
Tu-134A · Wing area
Single source127.3 m 2 (1,370 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] | 29 July 1963[source] |
|---|
| Developed into | Cirrus SR22[source] | — |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 72–84 passengers / 8,200 kg (18,078 lb)[source] |
|---|
| Propellers | 3-bladed[source] | — |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | — |
|---|
| National origin | United States[source] | Soviet Union[source] |
|---|
| Designer | — | Tupolev[source] |
|---|
| Built by | — | Kharkiv State Aircraft Manufacturing Company[source] |
|---|
| Status | — | In limited use[source] |
|---|
| Primary users | — | Aeroflot (historical) Soviet Air Force (historical) Russian Air Force Air Koryo[source] |
|---|
| Introduction date | — | 9 September 1967[source] |
|---|
| Developed from | — | Tupolev Tu-124[source] |
|---|
| Fuel capacity | — | 13,200 L (3,500 US gal; 2,900 imp gal)[source] |
|---|
| Airfoil | — | root: PR-1-10S-9 (15.7%); tip: PR-1-10S-9 (12%)[source] |
|---|
Maximum take-off; Tu-134A · Max takeoff weight
Single source