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Dassault Falcon 10



In 1968, Avions Marcel Dassault, decided to build a smaller version of the 20. Scaled down to 70 percent of the 20's size, possibly with U.S. powerplants and marketed through Pan American, would capitalize on the engineering and sales know-how learned from the Falcon 20 program. The result would be the Falcon 10, hopefully with a lower acquisition cost. Whereas the Falcon 10 wingspan, fuselage length and tail height all would be the desired 70 percent of the original Falcon 20 size, the volume inside the wing and fuselage available to carry fuel would only be 34 percent of that used in the 20. As a scaled down Falcon, the 10 would only hold 470 gallons of fuel.

To solve the problems Dassault would design a new, advanced wing, thick enough to hold sufficient fuel in internal tanks, yet still able to retain the high, critical Mach number and reasonable drag-rise characteristics associated with more conventional, thin airfoils.

It was decided that the Falcon 10 wing should be 13.5 percent thick at the root, retain much of its thickness (10 per-cent) up to the wing fence, and then slope to seven percent at the tip.


1st prototype


The first Falcon 10 (F-WFAL), powered by GE CJ610-1 engines, flew on December 1, 1970, and on June 1, 1971, set a 1,000-km closed-circuit speed record of 502.2 knots. A second prototype, with the Garrett TFE 731-2 engine, flew for the first time on October 15, 1971, and the number three Falcon 10 set a 2,000-km speed record in May 1973. In April 1973 the first production aircraft was flown.

The engineering team also incorporated advanced high-lift devices in the Falcon 10's wings to compensate for higher wing loading. (The Falcon 10's wing area is only 59 percent of the 20's, while the 10 lifts 64 percent of the 20's takeoff weight.) Full-span leading-edge devices, plus double-slotted Fowler flaps, combined with the advanced supercritical wing to produce a maximum lift capability for the Falcon 10 wing that is seven percent greater than the Falcon 20Fs and 35 percent greater than the Falcon 20E's.




Leading-edge slats and double-slotted Fowler flaps allow the Falcon 10 to operate out of many airports too small for either airliners or competitive corporate jets. FAR 36 noise standards are met, thanks to the quiet Garrett 731-2 turbofans. The airplane is certificated without the need for stick pullers to protect from overspeed, and stick shakers or pushers to protect against stall. Because the extras that Dassault included were expensive, the Falcon 10's price was higher than its light business jet competition.

Several of these aircraft are operated by the Aeronavale designated Falcon 10MER. They are used in general communications and liaison duties, as well as to give training to pilots of the Dassault Super Etendard carrier-based fighter. The Aeronavale's aircraft serve with ES3 at Hyeres and ES57 at Landivisiau.

Introduced in 1985 to supersede the Falcon 10 and certificated in December 1986, the Series 100 featured increased weights (Ramp and Max. Take-off), a fourth cabin window on the starboard side, bigger luggage compartment and a 'glass cockpit'. When production ceased in 1989 223 Falcon 10/100s had been delivered to customers in 24 countries.




1st prototype
Engines: 2 x Garrett AiResearch TFE 731-2 turbofan, 3230 lb / 1465 kg st
Wingspan: 42 ft 11 in / 13.08 m
Length: 45 ft 5 in / 13.85 m
Empty weight: 10,416 lb / 4725 kg
Max payload: 1945 lb / 886 kg
Max Mach: 0.87
Range 4 pax 45min res: 1800 nm / 2070 mi / 3330 km
Crew: 2-3
Passenger capacity: 7
Pax cabin length: 16 ft 5 in / 5.00 m
Pax cabin max width: 4 ft 9 in / 1.46 m
Pax cabin max height: 4 ft 11 in / 1.50 m
Pax cabin volume: 264.6 cu ft / 7.50 cu m
Front baggage: 12.35 cu ft / 0.35 cu m
Rear baggage: 24.7 cu ft / 0.70 cu m

Falcon 10

Engines: Garrett TFE 731-2, 3,230 lbs. thrust.
Length: 45 ft. 4 in.
Height: 14 ft. 6 in.
Wingspan: 42 ft. 11 in.
Aspect. ratio: 7.
Wing area: 259 sq. ft.
Wing loading: 70.7 lb/sq.ft.
Seats: 8.
Operating weight: 10,875 lbs.
Useful load: 7,425 lbs.
Payload with full fuel: 1,515 lbs.
Takeoff weight: 18,300 lbs.
Zero fuel weight: 12,460 lbs.
Power loading: 2.8 lb/lb.
Fuel capacity: 882 USG/5,910 lb.
Baggage capacity: 680 lbs.
Baggage area: 32 cu.ft.
Cabin pressure differential: 8.8 psi.
Cabin altitude at 45,000 ft: 8,000 ft.
Balanced field length: 4,300 ft.
Initial rate of climb: 4,200 fpm.
Gross takeoff climb gradient, one engine: 3.2 degrees.
Maximum operating altitude: 45,200 ft.
Maximum cruise (at 39,000 ft. and 16,000 lbs): 459 knots.
Normal cruise (at 39,000 ft. and 16,000 lbs.): 428 knots.
Long-range cruise (at 39,000 ft. and 6,000 lbs.): 428 knots.
Maximum range, full fuel (45-min res): 1,800 nm.
Stall speed (clean): 121 knots.  
Stall speed (gear, slats and flaps extended): 92 knots.
Crew: 2



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