Mikoyan-Gurevich MiG-25

Background and Requirements

During the Cold War, the strategic air defense of the Soviet Union fell to the Soviet Air Defence Forces (PVO), an independent service branch separate from the Soviet Air Force (VVS).^[1][2] The PVO was tasked with defending Soviet airspace against high-altitude American reconnaissance overflights and strategic bombers carrying free-fall thermonuclear weapons.^[1][2] By the late 1950s, overflights of Soviet territory by the Lockheed U-2 demonstrated that existing Soviet interceptors and surface-to-air missiles such as the SA-1 were inadequate for high-altitude interception.^[1] At the same time, the United States followed its subsonic Boeing B-47 Stratojet and B-52 Stratofortress bombers with the Mach 2 Convair B-58 Hustler and initiated development of the Mach 3 North American XB-70 Valkyrie and the Mach 3 Lockheed A-12 and SR-71 reconnaissance platforms.^[3][4]

At the beginning of 1958, Soviet defense authorities issued a formal operational requirement for a manned interceptor capable of reaching speeds of 3,000 km/h (Mach 2.8 to 3.0) and operating at altitudes up to 27 km (89,000 ft) to counter airborne targets flying between 0 and 25,000 metres.^[3][5] Both the Mikoyan and Sukhoi design bureaus responded.^[3] Mikoyan OKB-155 had accumulated experience through a sequence of heavy experimental interceptors in the late 1950s: the I-1, I-3U, I-7U, I-75, Ye-150, Ye-150A, Ye-152, Ye-152A, Ye-152P, and Ye-152M.^[6] The Ye-150 had been built specifically to test the Tumansky R-15 turbojet, and the twin-engine Ye-152 (designated Ye-166 for public records) set several world records.^[6] Although the Ye-152M was planned as a definitive heavy interceptor, the PVO selected the long-range Tupolev Tu-128 instead, and work on the single-engine Ye-152M was cancelled as design of the new twin-engine interceptor progressed.^[6]

Preliminary research at OKB-155 began in mid-1959 under chief project designer Mikhail Gurevich and deputy chief designer Lev Shengelaya.^[5][7][8] Soviet intelligence learned of the American Mach 3 A-12 reconnaissance program approximately a year later.^[9] On 10 March 1961, following a formal decree of the USSR Council of Ministers in February 1961, the State Committee for Aviation Technology (GKAT) ordered OKB-155 to commence full-scale design of the Ye-155 high-altitude platform in two distinct variants: the Ye-155P interceptor and the Ye-155R reconnaissance aircraft.^[2][5]

Design and Development

The Mikoyan design bureau evaluated several structural layouts for the Ye-155 airframe.^[7][10] One option featured side-by-side engines similar to the MiG-19.^[7][10] A second study placed one engine amidships with a ventral exhaust nozzle beneath the fuselage and a second engine in the aft fuselage, but this required extensive heat shielding and reduced internal fuel volume.^[7][10] A third layout stacked two engines vertically like the English Electric Lightning, but both the tandem and vertical layouts were rejected because the physical bulk of the Tumansky engines would create an excessively tall fuselage that complicated field maintenance.^[7][10] Placing the powerplants in underwing nacelles was also discarded due to the danger of severe yawing moments and directional instability in the event of an engine failure during flight.^[10] The bureau selected a side-by-side powerplant installation in the rear fuselage fed by lateral, variable-geometry rectangular intakes.^[7][10]

Designers considered variable-sweep wings, which would have improved manoeuvrability at subsonic speed at the cost of reduced fuel tank capacity, but the idea was soon dropped because the reconnaissance aircraft would operate at high speed and high altitude.^[11] A reconnaissance design with a variable-geometry wing was also rejected after its wing failed stability and rigidity tests.^[12] Lift-engine arrangements featuring auxiliary Kolesov RD36-35 vertical lift turbojets were evaluated to provide short-field performance from bomb-damaged runways, but the dedicated lift engines represented dead weight in horizontal cruise and displaced internal fuel.^[11][12] A proposed supersonic business and passenger transport variant carrying five to seven passengers at 2,500 km/h over distances up to 3,500 km was investigated between 1963 and 1965, but was ultimately abandoned.^[12][13] The design team, led by Mikhail Gurevich until his retirement in 1964 and subsequently by Nikolai Z. Matyuk, focused on a high-mounted trapezoidal wing and a twin-finned empennage.^[5][14]

Experimental prototype fabrication began at Machine-Building Plant Zenit (Factory No. 4223) in Moscow, while the Dubna Machine-Building Plant produced airframe subassemblies including wing panels, empennage components, pylons, and radomes.^[5][15] The first flyable prototype was the reconnaissance variant, designated Ye-155-R1.^[5][16] Equipped with Tumansky R-15B-300 engines, fixed 600-liter wingtip fuel tanks fitted with stabilizing fins, and attachment points for movable canards, it carried out its maiden flight on 6 March 1964 piloted by OKB-155 chief test pilot Aleksandr Fedotov.^[5][16] Fuel sloshing inside the wingtip tanks generated violent vibrations, and the wingtip tanks and canards were eliminated from later prototypes.^[17]

The interceptor prototype, Ye-155-P1, made its maiden flight on 9 September 1964 under test pilot Pyotr Ostapenko.^[5][18][19] Two prototypes of each version were assembled at the OKB experimental plant, followed by four pre-production reconnaissance aircraft (Ye-155-R3 through R6) and nine pre-production interceptors (Ye-155-P3 through P11) built at the Gorkii aircraft factory (Plant No. 21).^[5][20] Testing revealed considerable flaws in handling, an undersized hydraulic system and a centre of gravity that was hard to manage; the wings at first proved structurally too weak, and in certain flight conditions the ailerons reversed their effect. To solve these problems, designers increased vertical stabilizer surface area, reduced ventral fin depth, introduced an anhedral angle of -5 degrees to the outer wing panels, and programmed the differential all-moving horizontal stabilizers to act in roll (the scissors mode) alongside the ailerons at high dynamic pressure.^[5]

The aircraft was publicly unveiled on 9 July 1967 at the Domodedovo air show near Moscow, where three interceptor prototypes and one reconnaissance prototype conducted a low-level flypast.^[5][21][22] On 28 November 1967, Order No. 406s officially renamed the Ye-155P and Ye-155R as the MiG-25P and MiG-25R.^[5] State acceptance testing for the reconnaissance variant concluded in October 1969, and service trials for the interceptor variant finished on 27 April 1970.^[23] Official decrees adopting the MiG-25P into service with the PVO were ratified on 13 April 1972.^[5][24] On 3 April 1975, test pilot Stepan Mikoyan received the title Hero of the Soviet Union for completing state trials, while leading project test pilots Vadim Petrov and Aleksandr Bezhevets were also decorated as Heroes of the Soviet Union, and Norayr Kazaryan received the Order of Lenin.^[5]

Aviation World Records

Between 1965 and 1977, modified prototypes and production testbeds designated Ye-266 and Ye-266M established 29 official world aviation records certified by the Fédération Aéronautique Internationale (FAI) under Class C1 (III) for land-based jet aircraft of unlimited weight.^{[5][18][25][26]} In the official documentation supplied to the FAI, the prototypes and pre-production aircraft used for the records were designated Ye-266.^[5] The early record-breaking flights were performed using Ye-155-R1, Ye-155-R3, and Ye-155-P1 airframes that had been stripped of radar, sensors, and operational military hardware to reduce structural weight.^[5][27]

On 16 March 1965, Aleksandr Fedotov averaged 2,319.12 km/h over a 1,000 km closed circuit carrying zero payload, 1,000 kg, and 2,000 kg payloads.^[18] On 5 October 1967, test pilot Mikhail M. Komarov achieved 2,981.5 km/h over a 500 km closed circuit.^[18] On that same day, Fedotov attained an altitude of 29,977 m (98,350 ft) with a 1,000 kg payload, and the MiG later became the first aircraft to go higher than 35,000 m.^[25][26] On 4 June 1973, Boris Orlov set a time-to-height record by climbing to 20,000 m in 2 minutes 49.8 seconds.^[25] Ostapenko set records on the same date by reaching 25,000 m in 3 minutes 12.6 seconds and 30,000 m in 4 minutes 3.86 seconds.^[25] On 25 July 1973, Fedotov reached 35,230 m with a 1,000 kg load and achieved an absolute world zoom-climb altitude record of 36,240 m (118,900 ft) without payload.^[25] In the upper stratosphere, the turbojet engines flamed out due to lack of atmospheric oxygen, and the aircraft drifted on a ballistic trajectory over the apex, decelerating to an airspeed of 75 km/h before descending into denser air where the engines were restarted.^[25]

On 17 May 1975, the Ye-266M testbed (airframe Ye-155M re-engined with higher-thrust Tumansky R-15BF2-300 engines) set three world time-to-altitude records: climbing to 25,000 m in 2 minutes 34.2 seconds, to 30,000 m (both clean and with a 1,000 kg payload) in 3 minutes 10.0 seconds, and to 35,000 m in 4 minutes 11.7 seconds.^[28] On 22 July 1977, Fedotov climbed to 37,080 m carrying 1,000 kg and 2,000 kg payloads.^[29] On 31 August 1977, Fedotov flew the Ye-266M to an absolute world altitude record of 37,650 metres (123,520 ft) in a zoom climb at Podmoskovnoye, which remains the highest altitude ever achieved by an airbreathing jet-powered aircraft under its own power.^[26][30][31] Under the designation Ye-133, a MiG-25PU conversion trainer was flown by Svetlana Savitskaya between 1975 and 1977 to establish female world records, including an average speed of 2,683.45 km/h over a 15 to 25 km course on 22 June 1975.^[31][32]

Airframe, Materials, and Structure

Sustained flight at speeds between Mach 2.5 and Mach 3.0 produces intense aerodynamic surface heating, raising leading-edge skin temperatures to 250–290 °C and heating internal fuel tanks to 150–180 °C.^[7][33] Duralumin keeps its mechanical properties only up to about 130 °C, which ruled it out as a structural material.^[34] While American manufacturers turned to titanium alloys for the SR-71 and stainless-steel honeycomb for the XB-70, Soviet metallurgy in the early 1960s faced technological obstacles in rolling and crack-free welding of thin-walled titanium structures.^[7][35] OKB-155 selected heat-resistant stainless nickel steels for primary structural load paths.^{[5][7][14][35]} The finished MiG-25 airframe comprised 80% nickel-steel alloys by weight, 11% high-temperature aluminum alloys, 8% to 9% titanium alloys, and 1% other materials including composite dielectrics.^[5][36]

The steel airframe used specific alloys including VNS-2, VNS-4, VNS-5, VL-1, SN-3, EI-703, and EI-878, combined with heat-treated duralumin D19T and titanium alloy OT4-1.^[5] Structural connections relied on automatic and semi-automatic submerged-arc, spot, and manual argon-arc welding rather than traditional riveting.^[5][7] Automated welding allowed integral fuel tanks to form the primary load-bearing fuselage structure without separate tank bladders.^[5] Thermal radiation from the engine bays to the fuel tanks was mitigated by installing silver-plated steel heat screens between frames 10V and 13, accompanied by glass-fiber insulation mats (ATM-3 covered with ANTM fabric).^[5] Up to 5 kg of pure silver was electroplated onto heat-reflection panels across the engine and afterburner compartments.^[5] The cockpit canopy featured heat-resistant E-2 Plexiglas panels 20 mm thick on the forward flat windscreen and 12 mm thick on the side transparencies.^[5]

The fuselage is an all-welded, non-demountable semi-monocoque unit divided into five main sections across 57 transverse bulkheads (frames), of which bulkheads 1, 2, 3, 4, 5, 6, 6B, 7, 9, 10, 10A, 11, 12, 13, and 14 are heavy load-bearing structural members.^[5][10] Frame 1 supports the dielectric radome, which is canted downward at an angle of 4°12' relative to the fuselage reference axis.^[5] The forward pressurized compartment between frames 1 and 2 houses the cockpit with its KM-1M zero-altitude/130 km/h ejection seat and avionics equipment underneath.^[5] The bay between frames 2 and 3 houses additional pressurized avionics shelves above the nose landing gear bay.^[5] The central fuselage section between frames 3 and 12 is an integral welded nickel-steel tank unit containing fuel compartments Nos. 1 through 6.^[5] The rear fuselage section between frames 12 and 14 provides mounting attachments for the engine trunnions, vertical tail fins, ventral strakes, horizontal stabilizer bearings, speed-brake actuators, and flight control boosters.^[5] The tail cone attached to frame 14 houses the upper and lower speed-brake recesses and the braking parachute container.^[5]

The trapezoidal cantilever wing has an area of 61.4 m2, an aspect ratio of 2.94, a taper ratio of 3.1, a negative dihedral of -5 degrees, and a geometric wing setting angle of +2 degrees.^[5] Wing sweepback along the leading edge is variable on the interceptor, transitioning from 42°30' at the root to 41°02' along the outer panel, whereas reconnaissance variants employ a uniform leading-edge sweep of 41°02' (or 42°30' on early models).^[5] Wingspan measures 14.015 m on the interceptor and 13.38 m to 14.062 m on reconnaissance models.^[5] Each wing panel is attached to the fuselage at five points and incorporates three spars, two spanwise stringers, ribs, and an integral fuel tank divided into forward and aft cells.^[5] The removable wing leading edges are welded from titanium alloy. Two-section duralumin ailerons have a total travel of +/-25 degrees; to prevent aerodynamic aileron reversal caused by wing flexing at high dynamic pressures, trailing-edge flaps are supplemented by differential horizontal stabilizer deflection.^[5] Anti-flutter weights (60 kg steel mass-balance booms) are fitted to each wingtip.^[5][37]

The empennage comprises twin outward-canted vertical stabilizers and all-moving slab tailplanes.^[5] Each vertical fin has a surface area of 8 m2 (16 m2 total), a leading-edge sweepback of 54 degrees, an outward cant of 8 degrees (11 degrees relative to vertical), and symmetric TsAGI S-11S2M airfoils.^[5] The fin structures are fabricated from VNS-5 steel spars and heat-resistant AK-4 duralumin skins, carrying rudders with a travel of +/-25 degrees.^[5] Ventral strakes underneath each engine bay improve directional stability; the port ventral strake incorporates a downward-extending 1.3-meter runway contact probe inclined at 74 degrees to initiate automatic deployment of the braking parachute on touchdown.^[5] The all-moving horizontal stabilizers encompass 10.21 m2 with an 8.8-meter span, 50°22' leading-edge sweep, and symmetric TsAGI S-11S airfoils.^[5] Tailplane deflection ranges from -32 degrees to +13 degrees in pitch during takeoff and landing, dropping to -12.5 to +5 degrees at maximum airspeed, with +/-3°15' differential movement in roll.^[5]

Propulsion and Fuel Systems

The MiG-25 is powered by two Tumansky R-15B-300 single-shaft afterburning turbojets (upgraded during production and depot overhauls to R-15BD-300 standards).^[5][38] The R15B-300 was developed at OKB-300 under chief designer S. K. Tumansky from the experimental R15-300 engine, which had been used on the Ye-150 and Ye-152 prototype interceptors and the Tu-121 unmanned aircraft; the short-life KR15-300 engine of the Tupolev Tu-123 Yastreb reconnaissance drone was also derived from the R15-300.^[39] The R-15B-300 features an axial-flow five-stage compressor, an annular combustion chamber, a single-stage turbine, an afterburner duct, and a three-position convergent-divergent ejector nozzle.^[5][38] Sea-level static dry thrust is 73.5 kN (7,500 kgf), minimum afterburning thrust is 81.9 kN (8,350 kgf), and maximum afterburning thrust is 109.8 to 112 kN (11,200 kgf).^[5] Each engine measures 6,655 mm in length and 1,640 mm in diameter, with a dry weight of 2,700 kg.^[5] The R-15BD-300 incorporated improved turbine cooling, a dedicated turbostarter, and an accessory gearbox configured for constant-speed AC generators, raising the time between overhauls (TBO) from an initial 150 hours to 1,000 hours.^[5]

The powerplants are mounted in the aft fuselage behind frame 9, separated by a fire-resistant titanium partition.^[5] To provide ground crews access to the accessory gearboxes, both engines are rotated outward about their longitudinal axes by 13 degrees.^[5] The ejector nozzles are canted upward by 2°30' in pitch and toe-inward toward the fuselage centerline by 1°46' to align with aerodynamic flow lines.^[5] Because the nozzles are positioned closer together than their maximum outer diameters, three segments of the external nozzle flaps were omitted and replaced by a central fixed fairing.^[5] Engine airflow is delivered through rectangular variable-geometry side air intakes.^[5][10] An electro-hydraulic SRVMu-2A regulation system adjusts an upper movable ramp and a three-position lower intake lip according to Mach number and engine compressor pressure ratios.^[5][40] A water-methanol injection system sprays the mixture into the air intakes immediately ahead of the first compressor stage, cooling the incoming air, raising its density and increasing engine thrust.^[34][41]

The design cruising speed is Mach 2.35 at altitudes of 19,000 to 21,000 m (62,000 to 69,000 ft) under partial afterburner.^[33][42] The maximum speed of Mach 2.83 (3,000 km/h) is allowed for no more than 5 minutes because of the danger of overheating the airframe and fuel.^[42] At airframe temperatures reaching 290 °C, an instrument panel warning illuminates, requiring the pilot to reduce throttle.^[33][42] Although sufficient thrust was available to reach Mach 3.2, the engines tended to overspeed and overheat at higher airspeeds, possibly damaging them beyond repair.^[43][44] MiG-25s that reached Mach 3.2 had their engines replaced immediately after landing.^[43][44][45] Subsonic fuel consumption is heavy due to the engine compressor pressure ratio of 4.75, with specific fuel consumption measured at 1.25 kg/(kgf·h) in dry cruise and 2.75 kg/(kgf·h) with full afterburner.^[5][46]

The fuel system on interceptor variants consists of six fuselage tanks and four wing tanks with a total capacity of 14,570 kg (16,580 liters).^[5] Reconnaissance variants incorporate two additional tanks within the vertical fins, raising total internal fuel capacity to 15,000–15,245 kg (17,780 liters).^[5] The standard operational fuel is high-density T-6 kerosene (0.845 g/cm3), with TS-1, T-1, and RT permitted as secondary fuels with adjusted flight-range calculations.^[5][47] Pressurized technical nitrogen stored in eight spherical bottles (34.4 L total capacity) delivers an inert gas blanket over the fuel cells to prevent vapor ignition at high aerodynamic skin temperatures; on extended flights, the system switches to cooled engine-bleed air.^[5] Fuel from auxiliary tanks transfers into fuselage service tank No. 4, which houses a TN-10 air-driven turbopump and an auxiliary EtsN-93 electric pump.^[5] An inverted-flight accumulator tank maintains fuel flow for 15 seconds in dry power and 5 seconds in afterburner under zero or negative g-loads.^[5] A conformal jettisonable ventral fuel tank carrying 5,280 liters (4,450 kg) can be suspended beneath the fuselage center station.^[5]

Avionics, Flight Control, and Life Support

The flight control system uses irreversible hydraulic boosters powered by two autonomous circuits: a booster system (30 liters of 7-50s-3 silicone fluid) and a general utility system (53 liters).^[5][48] Each circuit has two NP-70A variable-displacement pumps mounted on different engines, and operating pressure is kept between 180 and 220 kg/cm2, with a nominal pump outlet pressure of 210 kg/cm2.^[5][48] The booster circuit powers the primary chambers of two BU-170 stabilizer boosters, one BU-170E aileron booster, and one BU-190 rudder booster, while providing emergency landing-gear braking.^[5] The general hydraulic circuit operates the secondary booster chambers, landing-gear extension and retraction, trailing-edge flaps, speed brakes, intake ramps, and nosewheel steering (MRK-20 mechanism providing +/-43 degrees in taxi mode and +/-8 degrees in takeoff/landing mode).^[5] Nitrogen gas accumulator bottles cushion pressure pulses, and a fuel-hydraulic radiator (TZhR-2415T) cools fluid circulating at temperatures up to 150 °C.^[5]

Flight control linkages combine mechanical cables in the dorsal fuselage spine with rigid push-pull tubes and bellcranks in the wings and empennage.^[5] Pitch feel and control displacement ratios are modulated by an electromechanical ARU-9 unit that alters the gear ratio between the control column and stabilizer according to dynamic air pressure and altitude.^[5] Automatic stabilization is governed by the SAU-155P flight control system (SAU-155R on reconnaissance variants) using RAU-107A electric series actuators.^[5][49] The system provides damping of short-period oscillations, automated ground-vectored target intercepts, programmed climb corridors, G-limit protection, and an emergency recovery function: pressing the 'Privedenie' button automatically returns the aircraft to wings-level horizontal flight from any unusual attitude.^[5]

Early interceptors carried the RP-25 Smerch-A (Product 720, NATO: Foxfire) monopulse radar, an evolution of the Tu-128's Smerch-100 system engineered under F. F. Volkov at OKB-339.^[5][50][51] Operating with vacuum-tube electronics and miniature nuvistors, the radar transmitted at a peak pulse power of 600 kW, providing jam-resistant target detection up to 100 km and tracking out to 50 km.^[5][50] Designed to track and target high- and fast-flying bombers and reconnaissance aircraft, the Smerch-A lacked look-down/shoot-down capability, which limited its effectiveness against low-flying targets.^[5][52] Following the compromise of the system in 1976, Soviet authorities accelerated development of the RP-25M Sapfir-25 (Product 25), adapted from the MiG-23ML's radar with a larger parabolic dish.^{[5][52][53][54]} The Sapfir-25 incorporated pulse-Doppler processing, look-down/shoot-down capability against low-altitude targets down to 50 metres, an AVM-25 analog computer, and tracking of up to six targets in track-while-scan mode.^{[5][53][54][55]}

Intercept command guidance for the MiG-25P was conducted primarily through the Vozdukh-1M automated command network via the onboard ARL-SM Lazur-M datalink receiver.^[5] Ground control radar networks processed tactical air situations and transmitted automated radio-command signals across 118 fixed VHF channels in the 100–150 MHz band, directing the aircraft along optimum intercept vectors at distances up to 350 km without requiring verbal radio contact.^[5] The Lazur-M display issued 128 discrete heading commands, 126 altitude commands (500 to 30,000 m), and 32 speed commands, which fed flight directors or coupled directly into the SAU-155 autopilot for automated weapon release.^[5] The MiG-25PD upgraded this system to the BAN-75 datalink operating in conjunction with the ground-based Luch-1 command guidance complex.^[5]

The environmental control system (ECS) bleeds approximately 800 kg/h of air from both engine compressors at 400 °C and 1.1 kg/cm2, routing it through primary air-to-air heat exchangers and a 2436T liquid-air evaporator.^[5] The air is split into a cabin line (240 kg/h cooled to -7 °C and pressurized to 0.45 kg/cm2) and an avionics equipment line (560 kg/h cooled to -20 °C at 0.075 kg/cm2) that feeds nine equipment bays.^[5] An ARD-57T cabin pressure regulator maintains cabin atmospheric conditions above 2,000 m, while an ART-56-7 thermostat regulates cockpit temperatures between +15 °C and +25 °C.^[5] The onboard evaporative liquid cooling system utilizes 260 liters of a water-ethanol mixture (colloquially termed 'Maslandovka' or 'Spirtovoz') carried in twin 125-liter tanks to cool the radar, generators, and radio equipment at high speeds, which earned the aircraft the nickname 'the supersonic booze carrier'.^{[5][10][56][57]}

Armament and Mission Equipment

As a dedicated interceptor, the MiG-25 carried no internal gun armament, relying entirely on heavy air-to-air missiles carried on four underwing APU-84-46 launch rails.^[5][58] The primary weapon was the Bisnovat R-40 (Product 46, NATO: AA-6 Acrid), a supersonic missile with a 70 kg high-explosive fragmentation warhead and a maximum firing range of 35 to 60 km against high-flying collision-course targets.^[5][59] The aircraft could carry four R-40R missiles, while the R-40T could be carried only on the two inboard pylons.^[5][58] Missiles were fired singly or in two-round salvoes separated by a 0.6-second interval in a fixed sequence: outer port, inner starboard, inner port, outer starboard.^[5] The upgraded MiG-25PD and PDS variants carried modernized R-40RD and R-40TD missiles, and could replace the two inboard R-40s with APU-60-2 twin rails mounting four R-60 or R-60M short-range infrared missiles for close combat.^{[5][54][58][60]}

Reconnaissance-bomber variants (MiG-25RB and derivatives) combined photographic or electronic intelligence suites with a high-altitude bombing capability.^{[5][59][61][62]} The Peleng-D (later Peleng-DR and Peleng-DM) autonomous navigation-bombing suite integrated an Anis-8 inertial navigation system, a DISS-3S (later DISS-7) Doppler ground-speed/drift sensor, and an Orbita-155 digital computer.^[5] The system enabled automated blind bombing against geographic coordinates from altitudes of 20,000 to 21,000 m at Mach 2.35.^{[5][62][63][64]} At supersonic speeds, free-fall bombs released from 20,000 m traveled forward on a ballistic trajectory for 38.8 to 40 km before impact.^[5][63][64] Up to 4,000 kg (and later 5,000 kg on modernized pylons) of specialized heat-resistant bombs were carried, typically four to eight 500 kg FAB-500M-62T high-explosive bombs or eight FOTAB-100-140 flash bombs on tandem MBD3-U2 racks beneath the fuselage and wings.^{[5][59][62][64]} Reconnaissance bombers were also wired to deliver tactical nuclear gravity bombs such as the RN-40.^[61][65]

The dedicated suppression of enemy air defenses (SEAD) variant, designated MiG-25BM (Product 02M, NATO: Foxbat-F), was developed from 1976 and deployed in 1982.^[5][66] Designed to suppress hostile air defense radar installations from the stratosphere to open corridors for tactical strike aircraft up to 500 km behind the front line, the MiG-25BM featured a 720 mm lengthened nose housing the Yaguar target acquisition and defense-suppression suite with the Sych-M passive radar homing and direction-finding station.^[5][66] Armament comprised four Raduga Kh-58U (AS-11 Kilter) anti-radiation missiles mounted on underwing AKU-58 launchers, capable of homing on enemy surface-to-air missile radars from ranges exceeding 40 to 120 km.^[5][66]

Flight Characteristics and Operational Limitations

According to official pilot documentation, practical airspeed limits for clean MiG-25 aircraft were set at 1,000 km/h indicated airspeed (IAS) below 5,000 m altitude (equivalent to Mach 0.83 at sea level), 1,100 km/h IAS between 5,000 m and 8,000 m, and 1,150 km/h IAS above 8,000 m when flying with the automated pitch control engaged.^[33] Dynamic pressure on the airframe is rated to a maximum limit of 7,000 kgf/m2 (at 1,200 km/h IAS), and exceeding 1,100 km/h IAS induces structural deformation, particularly inside the air intake regulation ramps.^[33] Flight at supersonic speed below 10,000 m is prohibited in peacetime.^[33] The corridor of audibility for the sonic boom generated on the ground beneath a supersonic MiG-25 extends across a lateral swath 40 to 80 km wide.^[33]

The operational ceiling without afterburner is 12,000 m (39,000 ft), rising to 14,000–15,000 m at subsonic speed with afterburner and up to 23,000 m (75,000 ft) at supersonic speeds.^[33][42] Exceeding the 23,000 m ceiling in operational units was prohibited.^[33] The aircraft stalls at an indicated airspeed of 240–245 km/h with the flight control system active, or 270–290 km/h in unassisted manual control.^[33] Time to climb to 10,000 m is 10 minutes in dry military power and 3.0 minutes with full afterburner, with a maximum sea-level rate of climb of 208 m/s (40,900 ft/min).^[33] Takeoff speed with maximum gross weight and internal fuel is 350–360 km/h, requiring a takeoff ground roll of 1,200 to 1,500 m, while landing approach speed is 360 km/h, touchdown speed is 270–290 km/h, and landing rollout with braking parachutes deployed is 800 to 900 m.^[5][67]

The maximum g-load rating was 2.2 g with full fuel tanks, with an absolute limit of 4.5 g.^[5][68] The airframe possesses a structural deformation threshold of approximately 11 g, but exceeding +4.5 g causes permanent plastic deformation of the wing spars and skin panels, and wingtip deflection up to 70 cm can induce aileron reversal and flat spins.^[5][53][68] Statistical fleet reliability records in the Soviet Air Defence Forces indicated a mean time between failures (MTBF) of 66 flight hours against an original military specification requirement of 8 hours, and Soviet operational units maintained operational readiness rates exceeding 90 percent throughout the 1970s and 1980s.^[69]

The Belenko Defection and Western Evaluation

Western intelligence first observed the MiG-25 during flypasts at the Domodedovo air show in July 1967.^[70] There it was assessed as a fighter-bomber and all-weather interceptor capable of speeds in excess of Mach 2.5.^[14][70] This assessment prompted concerns in the Pentagon that American tactical aircraft were outclassed, which accelerated development of the McDonnell Douglas F-15 Eagle under the F-X program.^[71][72]

On 6 September 1976, Flight Lieutenant Viktor Ivanovich Belenko of the 513th Fighter Aviation Regiment (11th Air Defence Army), stationed at Sakharovka air base near Chuguyevka in Primorsky Krai, defected to the West.^[5][73][74] Breaking away from a training formation at low altitude beneath radar coverage, Belenko flew across the Sea of Japan and landed his MiG-25P (bort number 31) at Hakodate Airport on Hokkaido, Japan.^[5][73][74] Short of fuel, the aircraft overshot the runway by 240 metres, damaging the nose gear.^[5][73][74] Belenko surrendered to local authorities and requested political asylum in the United States, which was approved by President Gerald Ford and later formalized under Private Law 96-62 signed by Jimmy Carter.^[5]

Fearing Soviet military intervention or covert operations to destroy the aircraft, the Japanese government deployed 200 soldiers and armored vehicles to secure Hakodate Airport, while the Maritime Self-Defense Force deployed five destroyers and patrol vessels in the Sea of Japan.^[5] On 25 September, a USAF Lockheed C-5A Galaxy transport flew the disassembled aircraft to Hyakuri Air Base near Tokyo.^[5][75] There, engineers and technical specialists from the United States Air Force Foreign Technology Division and Japanese defense agencies conducted a 67-day teardown and technical evaluation.^{[5][74][75][76][77]}

The inspection disproved prior Western assumptions regarding the aircraft's materials and combat capabilities.^[78] The airframe was built primarily of nickel-plated steel alloys rather than expensive titanium, explaining its empty weight of 20,000 kg and gross weight exceeding 36,700 kg.^[5][14][78] The avionics suite relied on vacuum tubes (nuvistors) rather than solid-state semiconductor integrated circuits.^[5][50] While Western analysts initially viewed this as obsolete, the tubes eliminated the need for specialized environmental cooling in the equipment bays and provided resistance to electromagnetic pulses (EMP) generated by nuclear detonations.^[5][50] The Smerch-A radar produced 600 kW of output power, but lacked look-down/shoot-down capability against low-altitude targets.^[50][52] Combat radius was limited to 300 km (186 miles) on internal fuel, and operational G-limits were restricted to 2.2 to 4.5 g.^[5][68]

On 15 November 1976, the disassembled components were packed into 30 crates, loaded onto the Soviet cargo ship Grigory Kozintsev at the port of Hitachi, and returned to Vladivostok.^[5][77] The Japanese government billed the Soviet Union $40,000 for airfield damage, handling, and shipping costs; the Soviet Union submitted an unfulfilled claim of $10 million for aircraft damage.^[5] Following its return, the airframe was inspected at the Gorkii aircraft factory and subsequently transferred to the Daugavpils Higher Military Aviation Engineering School in Soviet Latvia as an instructional airframe, where it was broken up for souvenirs in the late 1980s.^[5]

Belenko's defection compromised the MiG-25P's radar and missile systems and the Soviet identification friend or foe (IFF) system.^{[5][74][79][80]} On 4 November 1976, the Soviet government issued an urgent decree ordering an overhaul of the MiG-25 weapon system.^[5][52] OKB-155 developed the modernized MiG-25PD ('Product 84D', NATO: Foxbat-E), incorporating the RP-25M Sapfir-25 pulse-Doppler radar with look-down/shoot-down capability, a TP-26Sh infrared search and track sensor, an improved R15BD-300 engine, and the new Parol (Product 62) IFF cryptographic system.^{[5][52][54][79][81]} Existing MiG-25P interceptors were upgraded to this standard during depot overhauls as the MiG-25PDS.^[5][79][82]

Variants

Prototypes and testbeds encompassed several experimental configurations.^{[5][19][27][83]} The Ye-155R comprised two reconnaissance prototypes (Ye-155-R1 and R2) built in Moscow and four pre-production airframes (Ye-155-R3 to R6) built at Gorkii.^[5][20][83] The Ye-155P interceptor prototypes included Ye-155-P1 and P2 built in Moscow, followed by nine pre-production testbeds (Ye-155-P3 through P11) built at Gorkii.^[5][19][20] The Ye-266 designation was assigned to Ye-155-R1, Ye-155-R3, and Ye-155-P1 for official FAI world records, while Ye-266M applied to the Ye-155M re-engined with R-15BF2-300 powerplants.^[5][27] Izdeliye 99 comprised two modified airframes (one MiG-25P and one MiG-25R) used as flying testbeds for the Soloviev D-30F turbofan engines that later powered the MiG-31.^[5][84]

The primary interceptor variants began with the MiG-25P ('Product 84', NATO: Foxbat-A), a single-seat all-weather interceptor produced between 1971 and 1982 (460 built), equipped with the RP-25 Smerch-A1 radar and four R-40 missiles.^[5][7][85] The MiG-25PD ('Product 84D', NATO: Foxbat-E) entered production in 1978 (104 built up to 1984), featuring a 250 mm lengthened nose housing the RP-25M Sapfir-25 radar, a sub-nose TP-26Sh IRST, R-15BD-300 engines, and provision for R-60 missiles and a 5,280-liter drop tank.^{[5][7][54][86]} The MiG-25PDS designated 459 earlier MiG-25P interceptors converted to PD standards during factory depot overhauls between 1979 and 1983.^[5][82] Experimental interceptor variants included the MiG-25PDSL, a single aircraft modified with Beryoza-LM radar warning, Gardeniya-1FU active jammer pods, and chaff/flare dispensers, and the MiG-25PDZ, fitted with a retractable inflight refueling probe.^[5][82]

Reconnaissance and strike models began with the MiG-25R ('Product 02', NATO: Foxbat-B), a high-altitude daylight reconnaissance aircraft built in 1969–1970 fitted with five optical cameras and SRS-4 ELINT equipment.^[5][87][88] The MiG-25RB ('Product 02B', NATO: Foxbat-B) added the Peleng automatic bombing system and four to eight FAB-500M-62T bombs.^{[5][62][64][87]} The MiG-25RBV carried updated SRS-9 Virazh ELINT receivers and SPS-151 active jammers, while eight aircraft were fitted with FUKA radiation sampling pods under the designation MiG-25RR to monitor Chinese atmospheric nuclear detonations between 1970 and 1980.^[5][89][90] The MiG-25RBT ('Product 02T') introduced the Tangazh ELINT system and Parol IFF in 1978.^[5][90] The MiG-25RBN was a night-reconnaissance prototype equipped with NA-75 cameras and 10 photoflash bombs.^[5][90]

Dedicated electronic intelligence and radar-reconnaissance variants omitted optical cameras in favor of large fuselage antennas.^[5][90][91] The MiG-25RBK (NATO: Foxbat-D) carried the Kub-3M ELINT system, retained its bombing capability and was produced from 1971 to 1980; the MiG-25RBF was an RBK modernised with the Shar-25 ELINT system.^[34] The Kub-3M could pass the radio emissions it detected to a ground centre in real time.^[5][92] The MiG-25RBS ('Product 02S / Product 52', NATO: Foxbat-D) featured the Sablya-E side-looking airborne radar (SLAR), while the modernized MiG-25RBSh substituted the high-resolution Shompol SLAR with moving-target indication capabilities down to low altitudes.^[5][91] The MiG-25BM ('Product 02M / Product 66', NATO: Foxbat-F) was a defense-suppression aircraft carrying four Kh-58U anti-radiation missiles and a Yaguar avionics suite.^[5][66]

Dedicated two-seat conversion trainers were engineered with a stepped forward cockpit for the instructor pilot placed ahead of and below the main cockpit in a redesigned nose.^[5][31] The MiG-25PU ('Product 22', NATO: Foxbat-C) was the conversion trainer for interceptor units, built without radar and fitted with dual flight controls and cockpit target-simulation systems (173 built from 1969 to 1982).^[5][31][93] The MiG-25RU ('Product 39', NATO: Foxbat-C) was the trainer for reconnaissance-bomber crews, retaining the MiG-25R navigation system but omitting cameras, radar, and bomb pylons (48 built from 1970 to 1982).^[5][91][93] The MiG-25PU-SOTN was an optical/television chase plane modified in 1985 to record flight profiles and test K-36RB ejection seats for the Soviet Buran space shuttle program.^[5]

Operational History

The MiG-25 saw operational service across the Middle East, the Indian subcontinent, Eastern Europe, Central Asia, and North Africa.^{[5][94][95][96]} From March 1971 to July 1972, the Soviet Air Force deployed the 63rd Independent Air Detachment (Det 63), comprising two MiG-25R and two MiG-25RB aircraft, to Cairo-West Air Base in Egypt.^{[5][96][97][98]} The detachment flew reconnaissance missions over Israeli-held territory in Sinai roughly 20 times, in pairs at maximum speed and at altitudes between 17,000 and 23,000 m.^{[5][96][97][98][99]} Israeli F-4E Phantom II fighters attempted to intercept the reconnaissance pairs on multiple occasions, expending AIM-7E Sparrow missiles that failed to reach the high-altitude targets.^{[98][100][101]} Israeli MIM-23 Hawk surface-to-air missile batteries were unable to engage aircraft cruising above 20,000 m.^[102] A MiG-25 was tracked flying over the Sinai Peninsula at Mach 3.2 in the early 1970s, and the flight damaged its engines beyond repair.^[9][78][103] Soviet detachment 154 returned to Cairo with four MiG-25RB aircraft during the October 1973 Yom Kippur War, operating reconnaissance flights until late 1974.^{[5][98][100][104]}

During the 1970s, Soviet MiG-25RBSh aircraft conducted deep reconnaissance overflights of northern Iran in response to joint U.S.-Iranian Project Dark Gene surveillance flights along the Soviet southern border.^[105][106] In 1982, the 16th Tactical Air Army deployed a squadron of MiG-25PD interceptors belonging to the 787th Fighter Aviation Regiment to Eberswalde-Finow in East Germany, keeping two armed interceptors on continuous alert to shadow Lockheed SR-71 Blackbird flights over the Baltic Sea.^{[107][108][109]} In Afghanistan, the Soviet Air Force deployed 10 MiG-25RB reconnaissance aircraft to Shindand Air Base from 1986, sustaining zero combat losses throughout the Soviet-Afghan War.^[110][111]

Syria received a total of 2 MiG-25Rs, 16 MiG-25PDs, 8 MiG-25RBs and 2 MiG-25PU trainers.^{[5][112][113]} On 13 February 1981, the Israeli Air Force sent two RF-4Es over Lebanon as decoys for Syrian MiG-25 interceptors; the RF-4Es turned back using chaff and ECM pods, and two waiting Israeli F-15As shot down one of the MiGs with AIM-7F Sparrow missiles.^[5][114] On 29 July 1981, Israeli F-15As downed a second Syrian MiG-25PD over the Bekaa Valley, while a second Syrian MiG-25 fired two R-40 missiles that missed.^{[5][115][116][117]} On 31 August 1982, a Syrian MiG-25RB on a reconnaissance run was damaged by an Israeli ground-based MIM-23 Hawk missile and subsequently finished off by an Israeli F-15A.^{[118][119][120][121]} Syrian MiG-25s flew limited bombing sorties with FAB-500T bombs against rebel positions during the Syrian Civil War in 2012 and 2014, and all remaining airframes were destroyed on the ground by Israeli airstrikes following the fall of the Assad regime in early December 2024.^[122][123]

All confirmed air-to-air victories by the MiG-25 were achieved by the Iraqi Air Force.^[124] Iraq acquired 20 MiG-25PDs, 8 MiG-25RBs, and several PU trainers starting in 1979, forming the 84th, 96th, and 97th squadrons.^[5][62][125] During the Iran-Iraq War (1980–1988), Iraqi MiG-25PD interceptors shot down at least 15 Iranian aircraft: an F-5F over Eivan on 24 November 1982, an F-5E over Baghdad in December 1982, a C-130 in February 1983, an F-5E in April 1984, an F-4E on 21 March 1985, a second F-4E on 5 June 1985, a Fokker F-27 on 17 February 1986 (killing all 53 military personnel aboard), an EC-130 on 23 February 1986, an RF-4E on 10 June 1986, a second RF-4E in October 1986, and an Iranian Grumman F-14A Tomcat on 17 January 1987 with an R-40 missile.^{[5][126][127][128]} Iraqi MiG-25 ace Colonel Mohammed Rayyan accumulated 10 air combat kills (8 while flying the MiG-25PD) before he was shot down and killed by an Iranian F-14 in 1986.^[5][129] Outside Iran, an Iraqi MiG-25PD shot down an Algerian government Gulfstream on 3 May 1982.^[130][131] On 2 October 1986, an Iraqi MiG-25PD shot down a Syrian MiG-21RF.^{[132][133][134]}

Iraqi MiG-25RB aircraft conducted high-altitude supersonic bombing raids against Iranian strategic infrastructure, striking oil terminals at Kharg Island and dropping four 500 kg bombs per sortie on Tehran, Tabriz, Isfahan, and Qom.^{[62][135][136]} Iranian F-14A fighters claimed 10 MiG-25s destroyed, but Iraq confirmed only three combat losses: one MiG-25R shot down by an Iranian F-14A in June 1983 (Colonel Abdullah Faraj Mohammad), and one MiG-25RB downed by an Iranian HQ-2 surface-to-air missile on 25 February 1987 (Lieutenant Sayer Sobhi Ahmad, captured).^{[5][137][138][139]}

On the opening night of the Gulf War, 17 January 1991, an Iraqi MiG-25PDS flown by Lieutenant Zuhair Dawood of No. 96 Squadron shot down a U.S. Navy McDonnell Douglas F/A-18C Hornet piloted by Lieutenant Commander Scott Speicher using an R-40RD missile, representing the only confirmed Iraqi air-to-air victory of the conflict.^{[5][140][141][142][143]} On 19 January 1991, an Iraqi MiG-25PD evaded eight USAF F-15s and fired three missiles at two EF-111A Raven electronic warfare aircraft, forcing them to abort their mission and leaving attacking F-15Es without radar jamming support, resulting in the loss of one F-15E to ground fire.^[5][144] Later that day, two Iraqi MiG-25s were intercepted and shot down by USAF F-15Cs using AIM-7M Sparrow missiles.^[145][146] In the Samurra air battle on 30 January 1991, two Iraqi MiG-25s attacked two USAF F-15Cs, and as they withdrew, none of the ten air-to-air missiles fired by pursuing F-15s reached them.^{[147][148][149][150][151][152]}

Following the Gulf War, a USAF F-16D shot down an Iraqi MiG-25 violating the southern no-fly zone on 27 December 1992 using an AIM-120 AMRAAM, marking the first combat kill by an F-16 and the first operational AMRAAM victory.^{[5][153][154]} On 23 December 2002, an Iraqi MiG-25 shot down an armed USAF MQ-1 Predator drone over southern Iraq; the Predator fired an AIM-92 Stinger that missed, while the MiG's missile struck the drone, representing the first direct combat engagement between a manned aircraft and an armed unmanned aerial vehicle.^{[5][155][156][157][158]} In August 2003, several dozen Iraqi aircraft, including MiG-25s, were found buried in the sand.^[159] A MiG-25RB that had been buried in the sand near Al Taqaddum Air Base to prevent its destruction on the ground by coalition aircraft was found in 2003 and was one of two MiG-25s that a Lockheed C-5A Galaxy carried from Iraq to Wright-Patterson Air Force Base for examination.^{[5][121][159][160][161]}

The Indian Air Force took delivery of six MiG-25RBKs and two MiG-25RUs in 1981, which were operated by No. 102 Squadron 'Trisonics' based at Bakshi Ka Talab in Lucknow, Uttar Pradesh.^[96][162] The type was kept a guarded secret in India and was designated Garuda, after the mythical bird of Vishnu.^[5][163] Indian MiG-25s conducted extensive reconnaissance over Pakistan during the 1999 Kargil War and the 2001–2002 Operation Parakram.^[5][164] In May 1997, an Indian MiG-25RB flew faster than Mach 3 over Pakistani territory after a reconnaissance mission into Pakistani airspace, breaking the sound barrier at around 20,000 m; the Pakistani government contended that this was a deliberate attempt to show that the Pakistan Air Force had no aircraft that could come close to the MiG-25's cruising altitude.^[165] India denied the incident, but Pakistan's Foreign Minister, Gohar Ayub Khan, believed the aircraft had photographed strategic installations near Islamabad.^{[5][165][166][167]} On 24 October 1995, an Indian MiG-25 photographed a total solar eclipse from an altitude of 25,000 m.^[168][169] A lack of spare parts and India's acquisition of unmanned aerial vehicles and satellite imagery led to the retirement of its MiG-25 fleet.^[163][164] The retirement ceremony was held on 1 May 2006.^{[5][163][170]}

Libya imported 96 MiG-25PD, PU, and RBK aircraft between 1977 and 1982.^[171] Libyan MiG-25s intercepted U.S. Navy carrier aircraft during the 1981 and March 1986 Gulf of Sidra confrontations, engaging in non-firing maneuvering against Grumman F-14 Tomcats.^[172] Libyan MiG-25RBs also conducted high-altitude bombing runs during the Chadian-Libyan conflict.^[5] Grounded in the late 1990s due to lack of spare parts, several airframes were reactivated by the New General National Congress in 2014; on 6 May 2015, a reactivated MiG-25PU crashed near Zintan during a combat sortie.^[171][173]

Beginning in 1979, Algeria received at least 36 MiG-25s, including at least 18 MiG-25P interceptors, 10 MiG-25RB reconnaissance and strike aircraft, and 6 operational conversion trainers.^{[174][175][176]} During the Western Sahara conflict, Algerian MiG-25s flew reconnaissance over Moroccan-controlled territories and conducted high-speed runs over the Mediterranean and Andalusia in southern Spain, which were said to have prompted Spain to acquire F/A-18 Hornets.^{[177][178][179]} Algeria retired its operational MiG-25 fleet in July 2022, though two airworthy aircraft performed in the 70th Anniversary of the Algerian Revolution military parade in November 2024.^{[180][181][182][183]}

Following the 1991 dissolution of the Soviet Union, former Soviet republics inherited substantial MiG-25 inventories: Ukraine received 79 aircraft, Belarus inherited approximately 50, Kazakhstan received 16, Turkmenistan took 24, and Azerbaijan received 48.^{[5][184][185][186][187]} In June 1992, nine Russian pilots and technicians at Dallyar air base in Azerbaijan flew seven MiG-25RBs and one MiG-25RU to Russia under armed guard from Russian paratroopers to prevent their seizure by Azerbaijani forces.^[5] Azerbaijan deployed remaining MiG-25s for tactical bombing in the First Nagorno-Karabakh War, where at least three were lost, at least one of them to Armenian air defences, while one Azerbaijani pilot defected to Armenia with a MiG-25PD on 14 January 1993.^{[5][188][189][190][191]} Kazakhstan deployed two MiG-25RBs from the 609th Air Base at Balkhash to conduct reconnaissance over rebel movements during the 2000 Batken conflict in Kyrgyzstan.^[192]

Accidents and Flight Safety

During flight testing and early operational service, the MiG-25 experienced several fatal structural and propulsion failures.^[5] On 30 October 1967, test pilot Igor Lesnikov attempted a climb-to-altitude record in Ye-155-P1; exceeding safe speed thresholds, the aircraft banked uncontrollably to the left, and control column inputs exacerbated the roll due to aerodynamic aileron reversal, causing the aircraft to dive into the ground and killing Lesnikov.^[5] On 26 April 1969, the Commander of Aviation of the Soviet Air Defence Forces, Lieutenant General Anatoly Kadomtsev, was killed when a turbine blade detached on the left R-15 engine of his MiG-25P, severing accessory gearboxes and hydraulic lines and igniting an in-flight fire.^[5]

On 22 July 1971, Captain E. Starovoytov was flying a MiG-25RB from Shatalovo at 20,000 m and Mach 2.4 when an electrical short circuit severed DC generator power, discharging the emergency batteries within two minutes and causing a total shutdown of the SAU autopilot, radio, and all flight instruments.^[5] Diving through cloud cover without attitude reference, the aircraft clipped treetop branches with its lower air intake door before Starovoytov initiated an emergency zoom and ejected at 150 metres altitude.^[5] On 30 May 1973, test pilot A. Kuznetsov was killed in a MiG-25P at Akhtubinsk during a test flight at 1,100 km/h when the aircraft entered an uncontrolled rotation and his ejection failed because of the high rotation rate.^[5] On 30 June 1973, Major Maystrenko crashed during a low-altitude aerobatic practice run at Kubinka when his MiG-25 rolled at 540 degrees per second into the ground following an abrupt pitch command.^[5]

On 4 October 1973, test pilot Oleg V. Gudkov was killed at Ramenskoye investigating uncommanded roll oscillations in service MiG-25 airframes.^[5] During a high-speed pass, differential stabilizer actuator power proved insufficient against aerodynamic hinge moments, causing the slab tailplanes to jam and pitching the aircraft into an uncommanded axial roll that crashed into a textile factory building.^[5] Investigators determined that aerodynamic hinge loads on the horizontal stabilizer exceeded the hydraulic booster output, prompting OKB-155 to redesign all production stabilizers by shifting their rotational hinge axis forward by 140 mm, which resolved the problem.^[5]

Multiple operational accidents occurred during line service in the Soviet PVO.^[5] In 1977, two MiG-25 interceptors of the 82nd Fighter Aviation Regiment at Nasosnaya crashed: Senior Lieutenant Peleshenko was killed when his aircraft went into the Caspian Sea, and Senior Lieutenant Rakhimov died after misreading his altimeter during an instrument descent.^[5] On 24 June 1977, a MiG-25PU from unit 06984 in Arkhangelsk Oblast crashed in a flat spin, killing Captain Kondrushin and Senior Lieutenant Pyrochkin.^[5] On 10 January 1978, Captain Vitaly Konyukhov of the 786th Fighter Aviation Regiment was killed after stalling near Ivanovo while attempting an unassisted recovery.^[5]

The 933rd Fighter Aviation Regiment at Dnepropetrovsk (Kaydaki) recorded multiple serious incidents.^[5][193] On 8 December 1982, Colonel V. K. Gubanov crashed 500 m short of the runway after losing airspeed on final approach, striking landing beacon antenna arrays.^[5][193] In the summer of 1983, a MiG-25PU flown by crewmen Sklyarov and Lemesh was struck by ball lightning extending from the pitot tube to the tail fins, burning the antennas and knocking out onboard avionics before a dead-stick landing.^[5][193] On 16 July 1984, Lieutenant Colonel V. V. Semenov and Major E. A. Lemesh were killed in a MiG-25PU that entered a flat spin during instrument training.^[5][193] In 1986, Lieutenant Colonel O. S. Terpelivy landed safely after an engine fuel hose ruptured and ignited a major fire along the left fuselage side.^[5][193] In 1988, a formation collision between Captain Rassokhin and Senior Lieutenant Panfilov saw a wingtip anti-flutter weight tear off a nose radome, disabling the airspeed indicators.^[5][193]

On 1 September 1986 at Shchuchin, Senior Lieutenant V. Postupnoy landed a MiG-25BM with the landing gear retracted; having turned off the RI-65 voice warning unit to eliminate distractions during a low-fuel emergency approach, he forgot to drop the gear, and the airframe burned out on the concrete.^[5][194] On 19 September 1986, pilot G. V. Shepelev ejected from a MiG-25BM at 16,200 m and 1,070 km/h IAS following an engine turbine disk disintegration and subsequent dual-engine fire.^[5] On 13 May 1987 at Zaporozhye, a 738th Fighter Aviation Regiment MiG-25 caught fire on climbout due to turbine blade failure; the pilot ejected safely and the aircraft impacted a village chicken coop.^[5]

On 24 March 1989, Major G. I. Yanusov was killed ejecting from a MiG-25RB at 2,000 m over Vozzhayevka at supersonic speed; a pitot system failure led him to believe airspeed was dropping, and high dynamic pressure broke his limbs upon exiting the cockpit.^[5] In February 1990, a pilot flying a nocturnal stratosphere mission from Montchegorsk forgot to attach his pressurized helmet oxygen hose, lost consciousness from hypoxia at 15,000 m, and the aircraft descended under full afterburner until breaking up at 1,680 km/h IAS over Karelia.^[5] On 12 December 1996, a MiG-25PU carrying two senior regimental officers suffered a right main gear collapse during takeoff roll at Montchegorsk, skidding across the snow and hitting a road berm, crushing the forward cockpit and killing the pilot.^[5] On 2 July 2003, a MiG-25RB suffered a false engine fire warning on climbout over Montchegorsk; the pilot shut down the healthy engine, leaving insufficient thrust to clear a mountain ridge, steered the gliding aircraft toward a bog, and ejected successfully at an altitude of 80 metres.^[5][195]

Operators

Historical operators of the MiG-25 include the air forces of the Soviet Union, Russia, Ukraine, Belarus, Kazakhstan, Turkmenistan, Azerbaijan, Armenia, Algeria, Syria, Iraq, India, Libya, and Bulgaria.^[5][94][196] Until 2012 the Russian Air Force's remaining 20 MiG-25s were based at Voronezh and Montchegorsk, of which only about seven were airworthy.^[197] The last MiG-25s of the Russian Air Force flew at Montchegorsk from October 2012 until September 2013, and the decision to retire the type was made in December 2013.^[5][198] Ukraine operated 79 inherited aircraft until their retirement in 1996, while Belarus retired its fleet in 1995.^{[5][184][187]} The Bulgarian Air Force returned its three surviving MiG-25RBTs and one MiG-25RU to Russia in May 1991 in exchange for five MiG-23MLD fighters following the fatal crash of airframe No. 736 in April 1984.^[5][94]

The Indian Air Force operated six MiG-25RBKs and two MiG-25RUs from 1981 until May 2006, losing one MiG-25RBK in a crash on 3 August 1994.^[162][163] The Iraqi Air Force maintained 35 operational Foxbats in January 1991, but the majority were destroyed on the ground during Desert Storm, two were shot down in aerial combat, seven escaped to Iran, and surviving units were buried in desert sands in 2003.^{[199][200][201][202][203]} Algeria officially retired its MiG-25s from frontline service in July 2022, though a few remained flyable and were used in parades.^[180][182] As of 2026, standard international air order-of-battle surveys list no MiG-25 aircraft in active military operational service globally.^[94]

Aircraft on Display

Numerous preserved MiG-25 airframes are displayed in aviation museums globally.^{[5][204][205]} In Russia, the Central Air Force Museum at Monino exhibits prototype MiG-25R (bort 0200001) and MiG-25PD (bort 84030112).^{[205][206][207]} The Central Armed Forces Museum in Moscow displays MiG-25PD bort 84008895, while the Taganrog Aviation Museum exhibits MiG-25BM bort 66001012.^[5][208] Additional airframes are mounted on plinths at Nizhny Novgorod Victory Park (MiG-25PU bort 05), the Sokol Aircraft Plant, Yekaterinburg, Perm, and Dubna.^[5]

In the United States, the National Museum of the United States Air Force at Wright-Patterson Air Force Base in Dayton, Ohio, displays an incomplete Iraqi MiG-25RB (serial 020657).^{[121][160][161][209]} Recovered by American forces in 2003 buried in the sand without wings at Al-Taqaddum Air Base, it was flown to the United States aboard a C-5A Galaxy for technical analysis before being donated to the museum collection in December 2006.^{[121][160][161][209]}

In Europe, the Estonian Aviation Museum at Lange displays a MiG-25RBS (serial N02050740).^{[5][204][210]} The Riga Aviation Museum in Latvia preserves MiG-25RBS bort 0200004.^[211][212] In Ukraine, the State Aviation Museum at Zhulyany in Kyiv displays MiG-25RB bort 09, while the Military-Historical Museum of the Air Force in Vinnytsia preserves MiG-25RBS bort 17.^[5][213] In Belarus, the Stalin Line Museum at Loshany exhibits MiG-25RBS serial 02053164, the Minsk Aero Club Museum displays MiG-25BM bort 78 and MiG-25PU bort 19, and another MiG-25PU stands as a monument in Shchuchin.^{[214][215][216]}

In India, surviving MiG-25 aircraft from No. 102 Squadron are preserved at military installations: MiG-25R (KP-355) at the Indian Air Force Museum in Palam, Delhi; MiG-25R (KP-351) at the National Defence Academy in Pune; MiG-25U (DS-361) at Kalaikunda Air Force Station; MiG-25U (DS-362) at the Air Force Academy in Dundigal; and two aircraft at Trishul Air Force Base in Bareilly.^{[217][218][219][220][221]}

Civilian Flights and Popular Culture

Following the dissolution of the Soviet Union, the Gromov Flight Research Institute (LII) at Zhukovsky Airfield operated a civilian-contracted two-seat MiG-25PU for commercial high-altitude tourism.^{[5][222][223]} Paying civilian passengers were flown to altitudes between 24,000 and 27,000 m (79,000 to 89,000 ft) to view the curvature of the Earth and experience flight up to Mach 2.8, making it the fastest commercial passenger-rated aircraft experience in the world until the flights were terminated.^[222][223]

The MiG-25 featured prominently in Cold War media.^[5] The novel Firefox, inspired by Belenko's defection, and the 1982 film of the same name directed by and starring Clint Eastwood depict the theft of a fictional advanced Soviet fighter called the MiG-31 Firefox, and a MiG-25 appeared on the novel's cover. Other appearances include the 1977 Hong Kong spy film Foxbat. The aircraft was featured in the 1984 Soviet feature film Three Percent of Risk (Tri protsenta riska) starring Kirill Lavrov, and in the 2005 Russian television miniseries Nebesnaya zhizn.^[5] In the Transformers (G1) animated series, the Decepticon Blitzwing transforms into a MiG-25 and a Type 74 tank.

References

1. Rich and Janos 1994, p. 15.
2. MiG-25 'Foxbat', Guardian of the Soviet Borders, Yefim Gordon, עמ' 5
3. Gunston & Gordon 1998, p. 166. (Gunston, Bill; Gordon, Yefim (1998). MiG Aircraft since 1937. United Kingdom: Putnam Aeronautical Books. ISBN 1-55750-541-1.)
4. Stephan Wilkinson: Foxbat Follies. In: Air Power History. Autumn 2022, S. 28.
5. World Air Forces 2014 — 2014.
6. Gunston & Gordon 1998, p. 106. (Gunston, Bill; Gordon, Yefim (1998). MiG Aircraft since 1937. United Kingdom: Putnam Aeronautical Books. ISBN 1-55750-541-1.)
7. Gordon 2007
8. 苏联/俄罗斯米格-25高空高速战斗机：:空军世界 互联网档案馆的存檔，存档日期2007-12-28.
9. Spick 2000. (Spick, Mike (2000). The Great Book of Modern Warplanes. St. Paul, Minnesota: Motorbooks International Publishing. ISBN 0-7603-0893-4.)
10. MiG-25 'Foxbat', Guardian of the Soviet Borders, Yefim Gordon, עמ' 6
11. Lake 1998, p. 108. (Lake, Jon (1998). "Variant Briefing: MiG-25 'Foxbat' and MiG-31 'Foxhound'". World Air Power Journal. 34. London: Aerospace Publishing: 98–123. ISBN 1-86184-019-5. ISSN 0959-7050.)
12. MiG-25 'Foxbat', Guardian of the Soviet Borders, Yefim Gordon, עמ' 9–14
13. МиГ-25 административный — Испытатели (рус.). Дата обращения: 19 февраля 2022. Архивировано 19 февраля 2022 года.
14. L. Egenburg, A. Saweljew. Das G im Wörtchen "MiG": Michail Josifowitsch Gurjewitsch.. Fliegerrevue. 1993. ISSN 0941-889X. Je zde použita šablona {{Cite journal}} označená jako k „pouze dočasnému použití“.
15. Источник: Тихонов С. Г. «Оборонные предприятия СССР и России». М. «ТОМ», 2010 год. УДК 519.6 ББК 22.19 Т78, 2010, ISBN 978-5-903603-02-2
16. Belyakov and Marmain 1994, p. 398.
17. Belyakov and Marmain 1994, pp. 272–274.
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