- ON THIS PAGE :
- POWER PLANT
- FUEL CAPACITY
Power Plant
* The main
weakness of the Vautour was being under-powered. The aircraft
"deserved" to be fitted with 2 x 10,000 lb. st. thrust
engines, improving performance by far.
Prototypes
and Pre-Production aircraft: see the History chapter
Production aircraft (as built):
- Vautour IIA (30)
- * 23 with: two SNECMA Atar 101E-3 turbojets,
rated at 7,716 lb. st. each,(3,500 kgp, 34.32 kN) dry. (s/n 8 - 30, including all the 17 for Israel).
- * 1 with two SNECMA Atar 101E-5 turbojets, each
rated at 8,157 lb. st. (3,700 kgp, 36.28 kN) dry. (s/n 1)
- * 6 with two SNECMA Atar 101D-3 turbojets, each
rated at 6,217 lb. st. (2,820 kgp, 27.65 kN) dry. (s/n 2 - 7, these were assigned
to pilot training).
-
Vautour IIB (40)
- all with two SNECMA Atar 101E-3 turbojets.,/FONT>
-
Vauour IIN (70)
- * The two first with SNECMA Atar 101D-3 turbojets (s/n 301, 302).
- * 8 with two SNECMA Atar 101E-3 turbojets (s/n 303 and the seven for Israel).
- * 60 with two SNECMA Atar 101E-5 turbojets.
- Upgrades:
- * A part of IIB: with two SNECMA Atar 101E-5 turbojets,
- * Several Vautours, according to tests and trials, were fitted during service with diverse ATAR-series engines, possibly ATAR-8 and ATAR-9.
Fuel Capacity
1. The Vautour had a large fuel capacity, of almost 11,000 l' (8,800 kgs.), IIA variant, which was ca. 42% of the aircraft gross weight).
2. Although the engines were inferior in thrust, (as compared to
British conteporary turbines), a long-range flight, at high
altitude, resulted in an extraordinary good "specific range",
{ even better than that of the F-4 Phantom }.
3. Each engine was fed from its own set of fuel tanks.
4. The inner 17 fuel tanks had an automatic system to "isolate"
cells which caught fire or to neutralize leaks in the passages.
5. The pilot could direct or divert flow of fuel in case of
damaged pipes or engine malfunction.
6. The Vautour didn't have inflight refuelling devices. Only the experimental
(FR-AF) IIA(R) s/n 8, was tested as an air tanker for the Mirage-4.
- IIA
:
-
* Internal fuel (body and wings): 5,364 l'
in 17 cells.
-
* In weapon bay: 3,000 l' (2 x 1,500 l' tanks).
-
* External: 2 drop tanks of 1,300 l' or 600 l'.
-
*** Max. fuel: (5,364 + 3,000 + 2,600) = 10,964 l'
(8,771 kg).
- IIN
-
* Internal fuel: Ca. 750 kg. (= 938 l') LESS
than the single-seater, due to the double cockpit, i.e. approximately 4,426 l'.
-
* In the weapon bay & external tanks: as IIA.
-
*** Max. fuel: (4,426 + 3,000 + 2,600) = 10,026 l'
(~ 8,021 kg).
- IIB bomber
- *
Internal fuel {assumed even less than the N variant,
because of the large nose cockpit} guessed as , ca. 4,300 l'.
In the weapon bay: similar to the other variants (3,000 l').
external tanks: as IIA.
