Other designations or related variants include - MiG-31E.
Production/Prototype Quantities - Approx. 175 aircraft have been manufactured as of this writing, and though production has slowed in light of political and economic sanctions that have been levied in the Soviet Union, it does continue.
Cockpit - Two-seat configuration in separate cockpits. Forward cockpit accommodates pilot and rear cockpit accommodates weapon system operator. Cockpits are pressurized and air-conditioned. Pilot flies aircraft via conventional stick and rudder pedal controls. Both crew members sit on KM-1 ejection seats. Canopies are metal-framed units w/aft hinges and are opened hydraulically. Multi-transparency configuration includes three-piece windscreen. Aft cockpit displays are primarily via radar scope and related video display units (VDTs). Front cockpit instrumentation is primarily analogue and conventional.
Fuselage - General construction features virtually identical to those of the MiG-25 w/exception of considerably less titanium (leading edges, etc.). The latter deleted in consideration of lower top-end performance requirement and heavier emphasis on long range and endurance. Fuselage essentially semi-monocoque nickel steel alloy stressed-skin construction.
Lifting and Control Surfaces - Wing similar in construction and planform to that of MiG-25. Leading and trailing edge flaps of conventional construction. Also conventional trailing edge ailerons. All-moving slab-type horizontal tail surfaces and conventional vertical fins and rudders. Latter have slight outward cant. Large ventral fins also provided to accommodate directional stability requirements at high speed and high a.o.a. Leading edges of vertical tail surfaces and wing root extensions consist of many sections of dielectric material and contain various communications and EW antenna. Vertical tails each have a single-piece rudder. Construction materials appear to be same nickel steel alloy utilized on MiG-25—though titanium leading edge materials may have been changed. All control surfaces are hydraulically-actuated.
Landing Gear - Unconventional tricycle gear arrangement w/complex main gear bogie. Main gear retract slightly forward and up, and nose gear retract aft. Main landing gear is novel design optimized for improved rough field handling—though there also is some indication that the design also is optimized primarily to fit w/in the wheel well constraints of the lower fuselage. Main gear each have two wheels and tires—though separate, staggered axles and strut assemblies. Main gear ea. equipped w/disc brakes. Nose gear is steerable and equipped w/mud guard. A dual canopy drag chute is housed in a compartment in the ventral area of the empennage and is integral with the ventral fairing which runs down the aircraft centerline.
Miscellaneous Equipment - Retractable infrared sensor unit above nose and in front of windscreen (offset to right side of aircraft) and retractable laser range finder under nose. NATO Flash Dance radar has a search range of 186 mi. (300 km.) and a track range of 168 mi. (270 km.).
Powerplant/Fuel - Two medium bypass P. Solovyov Type D engines w/31,980 lb. (14,506 kg.) th. ea. Large aux. bypass doors mounted on the top side of each intake to accommodate mass flow requirements at high Mach. Intake design essentially rectangular. Superficially resembles intake seen on MiG-25, but somewhat larger. Like MiG-25 intake, however, lower lip is hinged to increase mass flow during taxi and at low speeds. MiG-31 almost certainly has done away w/water-methanol injection system. Internal fuel capacity of 5,385 gal. (20,382 lit.). Optional aux. tanks capable of providing an additional 820 gal. (3,100 lit.) can be carried on two wing pylons and fuselage centerline pylon.
Armament - Normal load is eight air-to-air missiles. Options are R-23/NATO AA-7 Apex (both R-23T w/infrared homing and R-23R w/radar homing); K-13/NATO AA-2 Atoll; R-60/NATO AA-8 Aphid; NATO AA-9 Amos; NATO AA-10 Alamo (both Alamo B w/infrared homing and Alamo C w/radar homing); and NATO AA-11 Archer on two wing pylons and six ventral fuselage points. Latter appear optimized primarily for Amos missile and no other type has been observed being carried there to date. What appears to be a single-barrel 30 mm. GSh-301 cannon is mounted in a large fairing on the right side of the fuselage, just above the main landing gear well.
Length - 72 ft. 9 in. (22.7 m.) w/pitot; 69 fl. 7 in. (21.7) w/o pitot.
Wingspan - 43 ft. 11 in. (13.7 m.).
Wing area - 685 ft.2 (63.6 m.2).
Height - 20 ft. 6 in. (6.4 m.).
Empty weight - 48,104 lb. (21,820 kg.).
Gross weight - 90,719 lb. (41,150 kg.).
Avg. combat th. to weight - .94.
Instantaneous turn capability - 16° to 18°/sec
Sustained turn capability - 8° to 10°/sec.
Max. speed @ s.l. - 932 mph (1.500 km/h).
Max. speed - 1,864 mph (3,000 km/h).
Service celllng - 60,000 ft. (18,701 m.)
Max. range - 2,485 mi. (4,000 km).
Notes - Combat thrust-to-weight ratio is 0.87 where combat wt. (50% int. fuel and four AA-9) is 73,220 lb. (33,212 kg.). Combat wing loading under same condition is 106.9 lb./ft2 (522.2 kg./m.2). Takeoff wt. clean is 85,760 lb. (38,900 kg.). Takeoff wt. w/4 x AA-9s is 90,719 lb. (41,150 kg.).