Mikoyan-Gurevich I-360 (SM-2)
Failure to meet predicted performance and poor reliability under test had led to some disenchantment with the large Lyulka TR-3 turbojet specified for the 1950 supersonic fighter programme. In consequence, the MiG 0KB elected to initiate development of a derivative of its contending TR-3-powered I--350 as a back-up programme, this, the 1-360 (SM-2), having close-paired Mikulin AM-5 small-diameter turbojets but being otherwise similar.
The SM-2 single-seat fighter proposal embodying an essentially similar wing to that of the I-350 with 55° sweepback at quarter chord (60° at leading edge). Powered by two AM-5F turbojets each with an afterburning rating of 2700kg and having an armament of two 37mm N-37D cannon in the wing roots, the first SM-2 - by now assigned the official designation of I-360 - was flown on 24 May 1952.
This was unique in having a T-type horizontal tail, and, on 25 June, it attained Mach=1.04 in level flight. Subsequent testing revealed that the wing tended to blanket the tailplane at high angles of attack, and, to rectify this deficiency, the tailplane was lowered to a mid point on the fin. Flight test (as the SM-2A) revealed little improvement and the surface was then further lowered to the base of the fin (as the SM-2B), this being accompanied by some increase in the vertical tail surface area, and satisfactory handling characteristics resulting.
The trials conducted (comprising 132 flights) ended in the loss of the aircraft in 1953 as a result of tail flutter at high speed, together with those of a further prototype, the SM-9 which had joined the test programme on 27 May 1952, were considered sufficiently successful to warrant immediate preparations for manufacture of a pre-series under the designation M1G-19.
Max take-off weight: 6820 kg / 15036 lb
Wingspan: 9.04 m / 29 ft 8 in
Length: 13.90 m / 45 ft 7 in
Height: 3.95 m / 13 ft 0 in