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]
TBM 900 · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | SOCATA TBM |
|---|---|---|
| Type | Light aircraft[source] | Executive transport and civil utility[source] |
| Manufacturer | Cirrus Aircraft[source] | SOCATA Daher[source] |
| Number built | 2,084 (through 2025)[source] | 1000 (as of October 2020 )[source] |
| Manufactured | 1999–present[source] | 1988–present[source] |
10.72 m (35 ft 2 in)[source]
Cruise; SR20-G3 · TAS
Single source155 kn (178 mph, 287 km/h) TAS[source]
Cruise; TBM 900 · long-range cruise at 9,449 m (31,001 ft)
Single sourceMaximum; TBM 900 · maximum cruise at 8,534 m (28,000 ft)
Single source611 km/h (380 mph, 330 kn) maximum cruise at 8,534 m (28,000 ft)[source]
467 km/h (290 mph, 252 kn) long-range cruise at 9,449 m (31,001 ft)[source]
TBM 900 · Range
Single sourceTBM 900 · with max fuel at long-range cruise and
Single source3,304 km (2,053 mi, 1,784 nmi) with max fuel at long-range cruise and 9,449 m (31,001 ft)[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]
TBM 900 · 1 × Pratt & Whitney Canada PT6A-66D turboprop engine 850 shp
Single source1 × Pratt & Whitney Canada PT6A-66D turboprop engine, 630 kW (850 shp)[source]
SR20-G3 · 828 ft/min (
Single source828 ft/min (4.21 m/s)[source]
TBM 900 · Wing area
Single source18.0 m 2 (194 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] | 14 July 1988[source] |
|---|
| Developed into | Cirrus SR22[source] | — |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 4-6 (including flight crew) / 636 kg (1,402 lb) max payload[source] |
|---|
| Propellers | 3-bladed[source] | 5-bladed Hartzell constant-speed propeller[source] |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | — |
|---|
| National origin | United States[source] | France[source] |
|---|
| Status | — | In production[source] |
|---|
| Primary users | — | French Army French Air and Space Force[source] |
|---|
| Introduction date | — | 1990[source] |
|---|
| Developed from | — | Mooney 301[source] |
|---|
| Fuel capacity | — | 1,100 L (290 US gal) usable[source] |
|---|
| Aspect ratio | — | 9.145[source] |
|---|
| Airfoil | — | root: RA 16-43; tip: RA 13.3-43[source] |
|---|
| Time to altitude | — | 9,449 m (31,001 ft) in 18 minutes 45 seconds[source] |
|---|
| Fuel consumption | — | 208 L/h (55 gal/h; 46 imp gal/h) / 164 kg/h (362 lb/h) at 593 km/h (368 mph; 320 kn) TAS, FL310, normal cruise, at 2,858 kg (6,301 lb)[source] |
|---|
| Take-off run | — | 726 m (2,382 ft)[source] |
|---|
| Landing run | — | 741 m (2,431 ft)[source] |
|---|