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]
Hawker 800 · Length
Single sourceConfiguration
| Specification | Cirrus SR20 | Hawker 800 |
|---|---|---|
| Type | Light aircraft[source] | Mid-size business jet[source] |
| Manufacturer | Cirrus Aircraft[source] | British Aerospace (BAe) (1983–1994) Raytheon (1994–2007) Hawker Beechcraft (2007–2013)[source] |
| Number built | 2,084 (through 2025)[source] | 650[source] |
| Manufactured | 1999–present[source] | 1983–2013 |
51 ft 2 in (15.60 m)[source]
Cruise; SR20-G3 · TAS
Single source155 kn (178 mph, 287 km/h) TAS[source]
Cruise; Hawker 800 · economical cruise at 39,000–43,000 ft (11,887–13,106 m)
Single sourceMaximum; Hawker 800 · max level speed and max cruising speed at 29,000 ft (8,839 m) / M0.87
Single source456 kn (525 mph, 845 km/h) max level speed and max cruising speed at 29,000 ft (8,839 m) / M0.87[source]
400 kn (460 mph, 740 km/h) economical cruise at 39,000–43,000 ft (11,887–13,106 m)[source]
Hawker 800 · with max payload
Single source2,580 nmi (2,970 mi, 4,780 km) with max payload[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]
Hawker 800 · 2 × Honeywell TFE731-5BR turbofan engines thrust each
Single source2 × Honeywell TFE731-5BR turbofan engines, 4,300 lbf (19 kN) thrust each[source]
Hawker 800 · Wing area
Single source374 sq ft (34.7 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] | 26 June 1983[source] |
|---|
| Developed into | Cirrus SR22[source] | — |
|---|
| Capacity | 3 passengers (4 using 60/40 flex seating in post-2012 models)[source] | 8 / 2,000 lb (907 kg) maximum payload[source] |
|---|
| Propellers | 3-bladed[source] | — |
|---|
| Stall speed | 56 kn (64 mph, 104 km/h) CAS[source] | 92 kn (106 mph, 170 km/h) in landing configuration at typical landing weight[source] |
|---|
| National origin | United States[source] | United Kingdom[source] |
|---|
| Status | — | In service[source] |
|---|
| Primary users | — | Japan Air Self-Defense Force Brazilian Air Force Royal Saudi Air Force[source] |
|---|
| Developed from | — | British Aerospace 125[source] |
|---|
| Fuel capacity | — | 1,248 imp gal (1,499 US gal; 5,674 L) total; 1,060 imp gal (1,273 US gal; 4,819 L) in wing integral tanks + 188 imp gal (226 US gal; 855 L) in rear under-fuselage tank[source] |
|---|
| Operating weight empty | — | 16,000 lb (7,257 kg)[source] |
|---|
| Maximum ramp weight | — | 27,520 lb (12,483 kg)[source] |
|---|
| Maximum zero-fuel weight | — | 18,000 lb (8,165 kg)[source] |
|---|
| Wing loading | — | 73.26 lb/sq ft (357.7 kg/m 2 )[source] |
|---|
| Thrust/weight | — | 0.313[source] |
|---|
| Take-off balanced field length | — | 5,620 ft (1,713 m) at MTOW[source] |
|---|
| Landing distance from 50 ft (15 m) | — | 4,500 ft (1,372 m) at typical landing weight and 6 pax[source] |
|---|
Maximum take-off; Hawker 800 · Max takeoff weight
Single source