Other designations or related variants include - MiG-29A, MiG-29UM, MiG-29UB, MiG-29SE, MiG-29SMT, MiG-29M, MiG-29M2, MiG-29K, MiG-29K2, MiG-29KUB, MiG-29OVT, MiG-35 and "product 9".

Production/Prototype Quantities - Approx. 500 aircraft have been manufactured, including a batch currently under construction in India. As a result of political and economic changes in the Soviet Union, production of the MiG-29 has slowed considerably.

Cockpit - Both single and two-seat MiG-29s have been built. Both types are equipped w/K-36D zero-zero ejection seats. Cockpit arrangement is conventional, w/basically analogue instrumentation and standard stick and rudder pedal controls. Cockpit is somewhat elevated and covered by an acrylic canopy and single-piece windscreen. Vision is nearly 360° w/some restriction directly aft. Canopy is hinged at the rear and opens vertically via pneumatic actuator. Two-seat aircraft, dimensionally identical to single-seat, has long, single-piece, two-transparency canopy that also opens vertically. Aft transparency of two-seat aircraft has a periscopic forward viewing unit mounted top and center. The periscope opens and closes automatically upon gear extension or retraction. A HUD is mounted above the instrument panel combing. There also is a helmet-mounted sighting system provided and integrated w/the weapon system. Miscellaneous standard instrumentation includes a horizontal situation indicator (HSI) and DME.

Fuselage - Conventional stressed-skin aluminum alloy construction. Engines housed in associated pods suspended from fuselage structural units. Significant blended-body design technique utilized. Fulcrum Cs have deeply curved dorsal hump which presumbably houses additional fuel and/or avionics. Still later versions with additional modifications have been noted.

Lifting and Control Surfaces - The conventional aluminum construction wings w/approx. 42° leading edge sweepback are equipped w/hydraulically-actuated, segmented leading edge flaps and Fowler-type slotted trailing edge flaps. Leading edge flaps have two-positions controlled by dedicated computer and driven as a function of Mach number and angle-of-attack. The hydraulically boosted ailerons are conventional single-piece units. Wing chord on centerline is 18 ft. 5 in. (5.6 m.); wing chord at tip is 4 ft. 2 in. (1.27 m.); wing anhedral is 2°. Six bolts fasten each wing to the fuselage. The twin vertical fins, w/a leading edge sweep angle of approx. 40°, are canted out 7° from the vertical, and are each equipped w/single-piece hydraulically-boosted rudders. Vertical fin dorsal extensions, on some aircraft, house flare/chaff dispensing units that now have become universally applied throughout the VVS. Late model MiG-29As have extended-chord rudders. All-moving, slab-type horizontal stabilators w/a leading edge sweep angle of approx. 50° provide both pitch and roll control (the latter being interfaced w/ailerons). Horizontal stabilator span is 25 ft. 6 in. (7.78 m.). The first 100 production MiG-29As also were seen w/extended ventral fins mounted near the horizontal stabilator attachment points. These since have been removed with no adverse effects. All control surfaces are actuated by pilot through conventional mechanical linkages and hydraulic boosters. Future MiG-29s are expected to be equipped w/fly-by-wire systems and at least one prototype FBW aircraft presently is flying. Present manual flight control system has stability augmentation driven by hybrid analog computer.

Landing Gear - Conventional tricycle arrangement w/single-wheel steerable main gear and dual-wheel nose gear. Main gear retract forward into wing root sections following a 90° rotational process that is mechanically accommodated. Nose wheels retract aft into well between engine intakes. All wheels are brake equipped, including the nose gear; no anti-skid system: mud/foreign object deflector/guard on nose gear. Main wheel tire size is 30.3 in. by 7.87 in. (770 mm. by 200 mm.) and nose wheel tire size is 20.86 in. by 3.93 in. (530 mm. by 100 mm.). Wheel track is 10 ft. 2 in. ( 3.10 m.); wheel base is 12 ft. 0 in. (3.67 m.). A pneumatically deployed dual canopy drag chute is housed in a container at the far aft end of the empennage section between the vertical tail surfaces. The maximum allowable gear-down speed is 311 mph (500 km/h). Hydraulically-actuated airbrakes are mounted on the top and bottom of the empennage.

Miscellaneous Equipment - Coherent NATO Slot Back pulse-Doppler radar w/look-down, shoot-down capability. Tracking range of a fighter-size target is 78 mi. (125 km.). Radar has conventional antenna (not phased-array) and operates in the 54 nanometer range. Known in Soviet service as the "Type 93" radar it is capable of tracking up to ten targets simultaneously and it is hardened against jamming. Additionally, it has a ground mapping capability. Both single and two-seat MiG-29s are equipped w/an IRST plus LR (infrared search-and-track system collimated w/a laser rangefinder; angular coordinates of target are fixed by the infrared sensor and distance is determined by a laser pulse unit) mounted in a large fairing just ahead of and offset to the right of the windscreen. There also is a helmet-mounted sight system. Other systems include the SRZO-2 (NATO Odd Rods) IFF and Syrena-3 radar warning equipment. Two-seat MiG-29UB has pulse-Doppler radar replaced by a small range-only radar unit in the extreme nose tip. Other miscellaneous combat systems have been deleted or changed. W/both single and two-seat configurations a number of dielectric covers are visible in a variety of positions, though most notably along the leading edge of the wing root extensions. Inertial navigation unit has two alignment modes. Radar altimeter antenna is mounted flush under nose.

Powerplant/Fuel - Two 18,300 lb. (8,301 kg.) th. Isotov RD-33 turbofans with hydromechanical controls. Engines are rt. and lt. peculiar and not interchangeable. They are fed by ramp-type rectangular intakes canted at approx. 9° from vertical w/straight-through ducting. Intake leading edge sweep-back angle is approx. 35°. Internal ramps control mass flow and shock wave formation. Each intake is equipped w/a single-piece, hydraulically-actuated door (hinged at the top forward edge) that completely closes off the intake and forces air to be ingested through a series of five large spring-loaded louver-type auxiliary intakes mounted on the upper surface of each wing root extension. This system permits operation from rough field environments and prevents FOD. These doors open automatically at 138 mph (222 km/h) and/or as aircraft weight comes off the landing gear during takeoff. Total internal fuel capacity is 1,153 gal. (4,365 lit.) divided among four fuel tanks as follows: F1 w/2,468.5 lb. (1,120 kg.); F2 w/1,893.8 lb. (859 kg.); F3 w/2,731.1 lb. (1,239 kg.); and W1 w/1,705.9 lb. (1,774 kg.)—giving a total of 8,799.3 lb. (3,991 kg.). Three 400 gal. (1,514 lit.) aux. fuel tanks can be carried (one on a centerline pylon, and one under each wing on wing hardpoints). NATO-standard high-pressure fuel receptacle located in left-hand wheel well.

Armament - Normal complement consists of up to six air-to-air missiles including 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-10 Alamo (both Alamo B w/infrared homing and Alamo C w/radar homing); and NATO AA-11 Archer on six wing pylons, one single-barrel 30 mm. GSh-301 cannon in the left wing root chine extension, and numerous combinations of bombs and air-to-ground rockets (57 mm., 80 mm., and 240 mm.)

Length - 56 ft. 10 in. (17.32 m.).

Wlngspan - 36 ft. 5 in. (11.36 m.).

Wing area - 410.07 ft.2 (38.1 m.2).

Height - 15 ft. 6 in. (4.73 m.).

Empty wefght - 18,025 lb. (8,175 kg).

Gross weight - 39,683 lb. (18,000 kg.).

Avg. combat th. to weight - 1.1.

Instantaneous turn capability - 20° to 22°/sec.

Sustained turn capability - 14° lo 16°/sec.

Max. speed @ s.l. - 805 mph (1,300 km/h).

Max. speed - 1,541 mph (2,480 km/h) at 30,000 ft. (9,351 m.) or Mach 2.3.

Rate of climb - 1 min. 0 sec to 65,000 ft. (20,260 m.)-this figure represents max. sea level rate of climb.

Service ceiling - 54,542 ft. (17,000 m.).

Max. range - 1,301 mi. (2,094 km.).

Notes - Max. thrust-to-weight ratio of MiG-29A is 1.1 to 1. Max. sustained g. is 9. Takeoff speed is 162 mph to 174 mph (260 km/h to 280 km/h); landing speed is 143 mph (230 km/h). Takeoff run is 770 ft. (240 m.); landing run is 1.925 ft. (600 m.).