Credit
USAF Greg L. Davis · Public domain · Resized · Public domain · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
E-6B · Length
Single source150 ft 4 in (45.82 m)[source]
Falcon 900B · Length
Single sourceConfiguration
| Specification | Boeing E-6 Mercury | Dassault Falcon 900 |
|---|---|---|
| Type | Airborne command and control[source] | Business jet[source] |
| Manufacturer | Boeing[source] | Dassault Aviation[source] |
| Status | In service[source] | Active service, in production[source] |
| Primary user | United States Navy[source] | — |
20.21 m (66 ft 4 in)[source]
E-6B · Height
Single source42 ft 5 in (12.93 m)[source]
Empty; E-6B · Empty weight
Single sourceMaximum take-off; E-6B · Max takeoff weight
Single source172,795 lb (78,378 kg)[source]
342,000 lb (155,129 kg)[source]
Empty; Falcon 900B · Empty weight
Single sourceMaximum take-off; Falcon 900B · Max takeoff weight
Single sourceE-6B · Combat range
Single source6,350 nmi (7,310 mi, 11,760 km)[source]
Falcon 900B · 3 × Honeywell TFE731 -5BR-1C turbofans thrust each
Single source3 × Honeywell TFE731 -5BR-1C turbofans , 21.13 kN (4,750 lbf) thrust each[source]
E-6B · maximum with multiple refuelings
Single sourceE-6B · on station at 1,000 nmi (1,200 mi; 1,900 km) unrefueled
Single sourceE-6B · with one refueling
Single sourceon station at 1,000 nmi (1,200 mi; 1,900 km) 10 hours 30 minutes unrefueled 28 hours 54 minutes with one refueling 72 hours maximum with multiple refuelings[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
| Number built |
|---|
16[source] |
>500[source] |
| Introduction date | August 1989[source] | — |
|---|
| First flight | 19 February 1987[source] | 21 September 1984 ( 1984-09-21 )[source] |
|---|
| Developed from | Boeing 707[source] | Dassault Falcon 50[source] |
|---|
| Powerplant | 4 × CFM International CFM56-2A-2 turbofan engines[source] | — |
|---|
| Wing loading | 112.13 lb/sq ft (547.5 kg/m 2 )[source] | — |
|---|
| Thrust/weight | 0.281[source] | — |
|---|
| Critical field length | 6,700 ft (2,042 m)[source] | — |
|---|
| Max effort take-off run | 5,400 ft (1,646 m)[source] | — |
|---|
| Landing run at max landing weight | 2,600 ft (792 m)[source] | — |
|---|
| Country of origin | Vereinigte Staaten[source]Country of design · Entwurfsland | — |
|---|
| National origin | — | France[source] |
|---|
| Primary users | — | French Air and Space Force Japan Coast Guard Nigerian Air Force Royal Malaysian Air Force[source] |
|---|
| Manufactured | — | 1984–present[source] |
|---|
| Developed into | — | Dassault Falcon 2000 Dassault Falcon 7X[source] |
|---|
| Capacity | — | 19 passengers[source] |
|---|
| Fuel capacity | — | 8,690 kg (19,160 lb)[source] |
|---|
| Aspect ratio | — | 7.63:1[source] |
|---|
| Stall speed | — | 158 km/h (98 mph, 85 kn) (wheels and flaps down)[source] |
|---|