MiG 23M / 2311 / MiG 23MF / MiG 23MS

The МЮ-23М took the place of the MiG-23S on the assembly lines. It was the long-awaited production aircraft whose arrival had been hin­dered by delays in the development of its systems (especially the radar) and its engine (whose thrust was inadequate to achieve the design parameters). Its wing chord was broader, leading to that distinc­tive dogtooth at the inner end of the leading edge and also a larger

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MiG-23MS (MiG ОКБ three-view drawing)

This MiG-23M carries R-23T and R-23R air-to-air missiles under the wing gloves. The four store stations under the fuselage are fitted with R-60Ts. The TP-23 infrared sensor is visible under the radome.

This MiG-23M has a type 2 wing, with its deeper chord and dog-toothed edge but no leading edge flaps. The four airbrakes are deployed.

The MiG-23MS was intended for export and equipped with less sophisticated radar and other systems

wing area. This was the type 2 wing, without leading edge flaps; but the MiG-23M was later retrofitted with type 3 wing, its four-part lead­ing edge flaps linked to those on the trailing edge as they retracted or extended.

It also had a different engine, the new Khachaturov R-23-300 rated at 8,135 daN (8,300 kg st) dry or 12,250 daN (12,500 kg st) with after­burner. And its systems were different: the S-23D-Sh forward-sector scanning and fire control system; the Sapfir-23-Sh radar; the TP-23 infrared sensor; the ASP-23D fire control device; and SAU-23A second – series automatic flight control system with the ARZ-1A feel computer on the pitch channel capable of taking the aircraft’s speed, altitude, and sweep angle into account.

Because of the missions allotted to the MiG-23M—interception, air combat, and attack of ground and naval targets—its weapon system included the GSh-23L twin-barrel cannon embedded under the fuselage on its easy-access hoisting tray and, at four store stations (two under the fuselage, two under the wing glove), radar-guided R-23R, IR-guided R-23T, R-13M air-to-air missiles, R-3A training missiles, B-8 rocket pods (firing S-8 rockets), UB-32 rocket pods (firing S-5 rockets), bombs of var­ious types and weights, submunitions dispensers, R-60 close-range air – to-air missiles, S-24 unguided air-to-surface rockets, and a pod housing the guidance system for air-to-surface missiles. The aircraft was decked out with an armament control panel.

Maximum internal fuel capacity was raised to 4,700 1 (1,241 US gal­lons) thanks to a fourth fuel tank in the rear fuselage The MiG-23M could also cany three drop tanks holding 7901 (209 US gallons) apiece, one under the fuselage and two under the wing glove) First piloted in June 1972 by A V. Fedotov, this model was the most popular MiG-23 and originated two export versions, the MiG-23MF and MiG-23MS, they carried less-advanced systems, armament (R-3S/R-3R missiles), and engines (the M1G-23MS used the R-27F2M-300), and their camouflage paint varied according to where they operated MiG-23M MF, and MS aircraft have taken part in several local conflicts in the Middle East and Afghanistan.

Specifications

Span (72° sweep), 7 779 m (25 ft 6 3 in); span (16° sweep) 13 965 m (45 ft 9 8 in); fuselage length (except probe), 15 73 m (51 ft 7 3 in); wheel track 2.658 m (8 ft 8 7 in); wheel base, 5 772 m (18 ft 11 3 in); wing area (72° sweep), 34 16 m2 (367.7 sq ft), wing area (16° sweep), 37 35 m2 (402 sq ft), takeoff weight, 15,750 kg (34,715 lb), max takeoff weight, 18 400 kg (40,555 lb), max takeoff weight with 790-1 (209-US gal) drop tank, 19,130 kg (42 160 lb), with two 790-1 (209-US gal) drop tanks 19,940 kg (43,950 lb); with three 790-1 (209-US gal) drop tanks, 20,670 kg (45 555 lb), internal fuel, 3 800 kg (8,375 lb), wing loading (72° sweep), 461-605 kg/m2 (94.5-124 lb sq ft); wing loading (16° sweep), 421 7-553 4 kg/m2 (86 4-113 4 lb/sq ft); max operating limit load factor (45° sweep), 8 at < Mach 0.85 7 at > Mach 0 85

Performance

Max speed in clean configuration (72 ” sweep), 2 490 km/h or Mach

2.35 at 12,500 m (1,344 kt at 41 000 ft); max speed in clean configura­tion (16° sweep), 935 km h or Mach 0.8 at 3,500 m (505 kt at 11 500 ft)