Dassault Mirage IIIV

Mating Mirage III aerodynamics with the then latest developments in vertical take-off and landing (VTOL) technology, the Mirage IIIV was evolved to meet the requirements of NBMR (NATO Basic Military Requirement) 3, and the first of two prototypes effected its first hovering trial on 12 February 1965. Possessing a substantially larger fuselage than that of the non-VTOL Mirage III, the first IIIV 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 M=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 grills covered the lift engines. On 12 September 1966, this second aircraft attained M=2.04 in level flight, but 11 weeks later, 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.

3-View

A three-view drawing (1703 x 1028)