Other designations or related variants include -
MiG-25M, MiG-25MB, MiG-25MP, MiG-25P, MiG-25R, MiG-25RB, MiG-25RBF, MiG-25RBK, MiG-25RBS, MiG-25RBSh, MiG-25RBT, MiG-25RBV, MiG-25U, MiG-25PU, Ye-133, Ye-155, Ye-26, Ye-266, Ye-266M.
Production/Prototype Quantities - Approx. 700 MiG-25s of all variants have been built. Production now has ended.
Cockpit - Interceptors are single-seat and equipped w/a KM-1 ejection seat w/zero height/93 mph (150 km/h) capability. It is assumed that the trainer derivative is similarly equipped. On the single-seat aircraft, the single-piece canopy is hinged to the right. The windscreen is a three-piece design primarily of glass. The cockpit is pressurized and airconditioned and the control system is conventional stick and rudder. All instrumentation is analogue and there are select vertical displays. The radar scope on radar-equipped aircraft (i.e. all but the trainer) is offset to the right side of the instrument panel. Miscellaneous equipment includes an RSB-70/RPS HF radio; an RSIU-5 VHF radio: and R-831 UHF radio; and an ARK-15 radio compass.
Fuselage - Primarily welded steel and titanium construction materials of otherwise conventional semi-monococque stressed-skin design. High-heat-sink areas, such as wing leading edges, empennage (from engine heat), intake lips. etc.. are primarily of titanium w/almost all other structure of steel w/aluminum where appropriate. Fuselage is generally circular in cross-section w/intakes of rectangular cross section. Hydraulically-actuated airbrakes are mounted both on top of and underneath the fuselage.
Lifting and Control Surface - The wings, of primarily steel construction w/titanium leading edges have a leading edge sweep angle of approx. 40° inboard and 38° outboard. Anhedral is 5°. Aspect ratio is low and the tips are provided thin pods w/a max. thickness of approx 11.8 in. (30 cm.) that accommodate both mass balance requirements and space for tip-mounted sensors. A single main fence is provided ea. upper surface at approx. mid-span w/a secondary fence a little further outboard Single-segment hydraulically-actuated Fowler-type flaps are mounted inboard of each hydraulically actuated aileron. All control linkages are mechanical. The horizontal tail surfaces w/50° leading edge sweep angle, are slab-type stabilators and provide both pitch and roll control. Twin vertical tails w/60° leading edge sweep angle and slight outward cant provide necessary vertical surface area tor high directional stability in high-speed flight. Each vertical tail is equipped w/a single-piece hydraulically actuated rudder. Each engine nacelle empennage area mounts a single large ventral fin (w/retractable sprung tail skids) tor improved directional stability at high Mach and high a.o.a.
Landing Gear - The tricycle landing gear is conventional in both appearance and design. Retraction of all three units is in forward direction. Retraction and extension are hydraulically actuated. Nose gear tires have a dimension of 25.6 in. (65 cm.) dia.; main gear tires of 47.25 in. (1.2 m.) dia. Main gear track is 23 ft. 1 in. (7.20 m.). There is a compartment for a dual-canopy drag chute located on the aft end of the empennage, between the vertical tail surfaces. It is pneumatically deployed.
Miscellaneous Equipment - Initial interceptor versions of the MiG-25 are equipped w/the RP-25 Smerch (NATO Foxfire) radar w/52 mi. (85 km.) range and w/pulse search-and-track capability; later interceptor versions are equipped w/the NATO High Lark IV radar w/pulse search-and-track and a multiple target indicating capability. Reconnaissance configurations are equipped w/broad spectrum sensors including optical and electronic. At least two different side-looking airborne radar systems are included in reconnaissance configurations w/MiG-25RB second-generation aircraft apparently totally dedicated to electronic intelligence of this kind—as it has no visible optical sensor capability of any kind. Other equipment includes SRZO-2 (NATO Odd Rods) IFF; SOD-57M ATC/SIF (w/antenna in right vertical fin tip); Syrena-3 radar warning system; ECCM and associated decoy and jamming equipment; SP-50 (NATO Swift Rod) ILS equipment; a PKI gunsight; a retractable IRST; and an MRP-56P marker beacon receiver.
Powerplant/Fuel - Currently two 30.864 lb. (14.000 kg.) th. Tumansky R-31-300 turbojet engines. Earlier aircraft were powered by two 24.728 lb. (11.217 kg.) th. Tumansky R-15B-300 (R-15BFZ-300 in record-setting aircraft) turbojet engines. Fed by ramp-type intakes w/electronically controlled variable-geometry ramps in throat to regulate mass flow and shock wave formation. Intake lower lip is hinged to increase mass flow during taxi and at low airspeeds. R-31 length is approx. 19 ft. 3 in. (6 m.); dia. of 4 ft. 9 in. (1.5 m.). Engines use water/methanol injection for pre-compressor section cooling to increase mass flow. Fuel quantity is 4,600 gal. (17,410 lit.) in 4 fuselage and 2 wing tanks. Aux. centerline tank optional.
Armament - Four wing pylons carrying a variety of ordnance including (interceptor variants)- R-23/NATO AA-7 Apex (both R-23T w/infrared homing and R-23R w/radar homing); K-13/NATO AA2 Atoll: R-60/NATO AA-8 Aphid; NATO AA-10 Alamo (both Alamo B w/infrared homing and Alamo C w/radar homing); NATO AA-11 Archer, and NATO AS-11 Killer.
Length - 71 ft. 6 in. (22.3 m.).
Wlngspan - 45 ft. 2 In. (14.1 m.).
Wing area - 666,2 ft.2 (61.9 m.2).
Height - 17 ft. 11 in. (5.6 m.).
Empty weight - 44,092 lb. (20,000 kg.).
Gross weight - 90,389 lb. (41,000 kg.).
Avg. combat th. to weight - .87.
Instantaneous turn capability - 16° to 18°/sec.
Sustained turn capability - 8° to 10°/sec.
Max. speed @ s.l. - 746 mph(1,200 km/h).
Max. speed - 1,864 mph (3,000 km/h) or Mach 2.85.
Rate of climb - 3 min. 30 sec. to 80,208 ft. (25,000 m.)
Service celling - 70.583 ft. (22,000); for MIG-25R 73,792 ft. (23,000 m.).
Max. range - MiG-25 interceptor (at supersonic speed) w/o aux. tank: 584 mi. (940 km.); MiG-25R (at supersonic speed) w/o aux. tank: 994 mi. (1,600 km.); MiG-25 interceptor (at supersonic speed) w.aux. tank: 798 mi. (1,285 km.); for MiG-25R (at supersonic speed) w/aux. lank: 1,305 mi. (2,100 km.).
Notes - Max. g-load is 5. Takeoff run is 4,010 ft. (1,250 m.); landing run is 2,567 ft. (800 m.).