01 Mirage IIIV
Musée de l'Air et de l'Espace (MAE), Le Bourget.
This supersonic VTOL prototype was powered by a SNECMA-modified Pratt & Whitney JTF10 turbofan, redesignated TF-104B and providing cruise thrust, vertical thrust being provided by a battery of eight 1600kg Rolls-Royce RB162-1 engines mounted in pairs in the centre fuselage.
Wing root chord was increased by comparison with that of the non-VTOL Mirage, resulting in compound sweep. Following replacement of the 6300kg TF-104 by the TF-106A3 offering 7600kg, the IIIV effected its first transition to horizontal flight on 24 March 1966 and later attained speeds up to Mach 1.35.
The second prototype was flown on 22 June 1966. This was powered by an 8400kg TF-30 propulsion turbofan, and side-hinged doors rather than aft-hinged grilles covered the lift engines. On 12 September 1966, this second aircraft attained M=2.04 in level flight. But on 28 November 1966, the second prototype was lost in an accident. The aircraft became uncontrollable (in crabbing/sideslip flight tests), and the test pilot ejected and survived.but on 28 November, it was destroyed in a crash.
The production Mirage IIIV was intended to combine a 9000kg TF-306 propulsion engine (built by SNECMA) with eight 2200kg RB162-31 lift engines, and was to be optimised for the tactical strike role, with a low-level M=0.92 attack mode and a 467km combat radius with a 907kg nuclear payload. The development programme was suspended after the loss of the second aircraft and finally abandoned.
01 Mirage IIIV
Musée de l'Air et de l'Espace (MAE), Le Bourget.
This supersonic VTOL prototype was powered by a SNECMA-modified Pratt & Whitney JTF10 turbofan, redesignated TF-104B and providing cruise thrust, vertical thrust being provided by a battery of eight 1600kg Rolls-Royce RB162-1 engines mounted in pairs in the centre fuselage.
Wing root chord was increased by comparison with that of the non-VTOL Mirage, resulting in compound sweep. Following replacement of the 6300kg TF-104 by the TF-106A3 offering 7600kg, the IIIV effected its first transition to horizontal flight on 24 March 1966 and later attained speeds up to Mach 1.35.
The second prototype was flown on 22 June 1966. This was powered by an 8400kg TF-30 propulsion turbofan, and side-hinged doors rather than aft-hinged grilles covered the lift engines. On 12 September 1966, this second aircraft attained M=2.04 in level flight. But on 28 November 1966, the second prototype was lost in an accident. The aircraft became uncontrollable (in crabbing/sideslip flight tests), and the test pilot ejected and survived.but on 28 November, it was destroyed in a crash.
The production Mirage IIIV was intended to combine a 9000kg TF-306 propulsion engine (built by SNECMA) with eight 2200kg RB162-31 lift engines, and was to be optimised for the tactical strike role, with a low-level M=0.92 attack mode and a 467km combat radius with a 907kg nuclear payload. The development programme was suspended after the loss of the second aircraft and finally abandoned.