NATO reporting name: Fulcrum
Indian Air Force name: Baaz (Eagle)

TYPE: Multirole fighter.

PROGRAMME: Production of land-based MiG-29s ended in mid-1990s after some 1,600 aircraft, leaving substantial stock of semi-complete airframes available to meet export orders. Most recently, Yemen received MiG-29SMTs and MiG-29UBT trainers in late 2004, this being the first delivery of these variants. Activity currently centres on upgrades for existing aircraft.
Prospects for new production were long dependent upon Indian order for carrier-based MiG-29K. By 2001 — in advance of formal order — MiG was constructing two pre-series MiG-29Ks, one MiG-29KUB and static test airframe in single-seat configuration. Sokol plant contracted in 2001 to build folding wing and nose section for production aircraft.
Eventually, on 20 January 2004, contract signed with India for 12 MiG-29Ks and four MiG-29KUB two-seat trainers, worth in excess of US$700 million, for delivery by 2007-08. Option exists for further 30 to be supplied by 2015. Production by LAPIK at Lukhovitsy. At time of contract signature, detailed technical specification still to be finalised.
Following data generally for MiG-29K. Earlier versions described in Jane's Aircraft Upgrades. However, Algeria reported in January 2006 to have purchased 36 MiG-29SMTs and taken option on further 20; if new-build, these would require resumption of MiG-29 in its land-based form.

CURRENT VERSIONS: MiG-29K: (Factory index 9.31; K for korabelnyy; ship-based) Maritime version, used for ski-jump take-off and deck landing trials on carrier Admiral of the Fleet Kuznetsov (formerly Tbilisi), beginning 1 November 1989; two new-build prototypes, using second-generation MiG-29M structure; completely redesigned, mainly steel, wing using modified aerofoil section and of increased area (increased span, reduced leading-edge sweep) with double slotted flaps, drooping flaperons and more powerful leading-edge flaps; new spar in front of original wing box; new strengthened centre-section without overwing louvres; upward-folding outer wing panels; RD-33K turbofans with 92.2 kN (20,723 lb st) contingency rating for ski-jump take-offs. Fuel capacity reduced to 5,670 litres (1,498 US gallons; 1,247 Imp gallons). First flown (16188 ‘311’) 23 June 1988; second prototype was 27579 ‘312’.
State Acceptance Trials suspended due to funding difficulties, early 1992. Further development ended initially when not selected for deployment on Admiral of the Fleet Kuznetsov, but resumed at Zhukovsky in September 1996, in expectation of order from India. First prototype currently grounded; second returned to flight status in support of MiG-29M programme. Proposed naval MiG-29KU (9.62) trainer derivative with two separate stepped cockpits remained unbuilt.
‘MiG-29K-2002’: (Factory index 9.41) The original MiG-29SMTK (factory index 9.17K; effectively a MiG-29SMT with the 9.31's folding wing and landing gear), previously offered to India along with the former helicopter carrier Admiral Gorshkov, is understood to have been replaced by a new, multirole, carrierborne variant based more closely on the MiG-29K/M, albeit without the expensive AI-Li alloys. Development of new MiG-29M variants (single- and two-seat) continued in 2003 with MiG-29OVT (thrust-vectoring ground testbed) and MiG-29M2 (29MRCA) which first flew on 26 September 2001 after conversion to tandem configuration.
With a MIL-STD-1553B-type bus and open systems avionics architecture, the MiG-29K-2002 is compatible with a wide range of Russian and Western weapons, and may feature the colour displays and GPS-based navigation system of the MiG-29SMT. This variant, possibly designated MiG-29 MTK, is claimed to be able to perform 90 per cent of its missions with a 10 kt (18 km/h; 11 mph) wind-over-deck, even in tropical conditions using new autothrottle. Notable features of the new aircraft are its improved wing with enlarged trailing-edge flaps, digital FBW system, emergency fuel draining and much-reduced folded span of 5.80 m (19 ft 0¼ in), achieved by positioning the fold line much closer in to the wingroot, and by adding upward-folding tailplanes. The aircraft can also fold its radome (up and back), reducing overall length to 14.13 m (46 ft 4¼ in). Accordingly, 44.570-tonne Admiral Gorshkov, which India has also purchased (as INS Vikramaditya), can carry a full air wing of 24 MiG-29Ks (plus six helicopters), or (according to some sources) as many its 30.
A projected MiG-29K-2008 upgrade configuration could add Zhuk-MF phased-array radar, RD-133 turbofans, a computer upgrade and additional electro-optic, radar, IIR and reconnaissance pods, together with take-off performance improvements. In December 1999, it was reported that India had selected the MiG-29K for use aboard Admiral Gorshkov, with a quantity of Kh-35 anti-ship missiles and Kh-31P ARMs. Proposed local manufacture by HAL appears no longer to be viable.
MiG-29KUB: (Factory index 9.47) Revised carrier-borne two-seat trainer design offered to India, based on MiG-29K-2002 with reduced-span, inboard wing fold and folding tailplanes. Assumed to feature original stepped tandem cockpits of MiG-29KU. Some reports suggest enlarged tailfins with integral fuel tanks.
MiG-35: Most recent use of this designation adopted in 2005 when MiG-29OVT upgrade was redesignated for possible new manufacture in India to meet local requirement for 126 aircraft. Offers high commonality with Indian Navy aircraft; RD-33MK thrust vectoring engines; and electronically scanned radar.

DESIGN FEATURES: Emphasis from start on high manoeuvrability, to counter US F-15, F-16 and F-18, with target destruction at distances from 200 m (660 ft) to 32 n miles (60 km; 37 miles), and with effective air-to-surface capability. All-swept mid-wing configuration, with wide ogival wing leading-edge root extensions (LERX), 40 per cent of lift provided by lift-generating centre-fuselage, twin tailfins carried on booms outboard of widely spaced engines with wedge intakes. Gap between roof of each intake and skin of wingroot extension for boundary layer bleed.
Fire-control and mission computers link radar with laser range-finder and infra-red search/track sensor, in conjunction with helmet-mounted target designator. Difficult to get into stable flat spin, reluctant to enter normal spin, recovers as soon as controls released; wing leading-edge sweepback 73° 30' on LERX, 42° on outer panels; anhedral approximately 3°. Tailfins canted outward 6°; leading-edge sweep 47° 50' on fins, 50° on horizontal surfaces; anhedral 3° 30'. Fins canted outwards 6°. Engine replacement time 2 hours; preflight preparation 20 minutes. Design flying fife 2,500 hours.

FLYING CONTROLS: Digital fly-by-wire.

STRUCTURE: Approximately 7 per cent of airframe, by weight, of composites; remainder metal; three-spar wings with three ‘false spars’ two ahead of, one behind, torsion box; 16 stringers and skins reinforced by stringers; trailing-edge wing flaps, ailerons and vertical tail surfaces of carbon fibre honeycomb; approximately 65 per cent of horizontal tail surfaces aluminium alloy, remainder carbon fibre; semi-monocoque all-metal fuselage built around 10 mainframes in three subassemblies, with forward (frames 1 to 3), centre (frames 4 to 7) and rear sections, the latter including the engine bays; fuselage sharply tapered and downswept aft of flat-sided cockpit area, with ogival dielectric nosecone mounting PVD-18 main pitot boom (PVD-7 auxiliary pitot mounted on side of nose); small vortex generator each side of nose helps to overcome early tendency to aileron reversal at angles of attack above 25°; tail surfaces carried on slim booms alongside engine nacelles.

LANDING GEAR: Hydromash retractable tricycle type, with oleo-pneumatic shock-absorbers. Mainwheels retract forward into wingroots, turning through 90° to lie flat above leg; nosewheels, on trailing-link oleo, retract rearward between engine air intakes. Hydraulic retraction and extension, with mechanical emergency release.

POWER PLANT: Two Klimov/Sarkisov RD-33MK Morskaya Osa (Sea Wasp) ‘marinised’ turbofans, each 85.3 kN (19,180 lb st) with afterburning. Engines mounted 4° nose-up, and nacelles toe-in by 1° 30'. Engine ducts canted at approximately 9°, with wedge intakes, sweptback at approximately 35°, under wingroot leading-edge extensions. Refuelling probe and increased internal capacity.

ACCOMMODATION: Pressurised cockpit enclosed by frames 1 and 2. Pilot only, on 16° rearward-inclined K-36DM Series 2 zero/zero ejection seat, giving -14° view forward over the nose, and under hydraulically actuated, rearward-hinged transparent blister canopy in high-set cockpit. Sharply inclined one-piece curved windscreen of electrically de-iced triple glass. Three internal mirrors provide rearward view.

SYSTEMS: Two independent hydraulic systems powered by NP-103A variable-displacement pumps, driven by the engine accessory gearboxes, pressurised to 207 bar (3,000 lb/sq in), with 80 litres (21 US gallons; 17.5 Imp gallons) fluid. Main system powers one chamber of each control surface actuator, leading-edge and trailing-edge flaps, stick-pusher, artificial feel unit, landing gear extension/retraction, nosewheel steering and APU exhaust door; back-up system powers second chamber of each control surface actuator and stick-pusher, and can be powered by an emergency NS-58 pump.
Three separate pneumatic systems, with main system powering the wheel-brakes, canopy, fuel shut-offs and brake parachute actuator and jettison; and emergency system operating mainwheel brakes, and allowing emergency gear extension; final system pressurises hydraulic tanks and avionics bays.
Air conditioning uses bleed air cooled by heat exhangers and turbocooler. System also pressurises pilot’s suit, demists screen and cools the gun bay.
Ozh-65 glycol-based liquid cooling system for radar.

AVIONICS: Expected to incorporate French, Russian and Indian components integrated by Elektroavtomatika or RPKB.
Radar: Phazotron-NIIR Zhuk-M (Zhuk-MEh in export form for MiG-29K and -29SMT). N011M Bars offered as basis for alternative.
Mission: Helmet-mounted sight.

ARMAMENT: R-73 (AA-11 ‘Archer’), R-27 (AA-10A ‘Alamo’), and/or R-77 (AA-12 ‘Adder’) AAMs; Kh-35 (AS-20 ‘Kayak’), Kh-31 (AS-17 ‘Krypton’) and Kh-29 (AS-14 ‘Kedge’) ASMs; KAB-250KR TV-guided bombs; FAB-500 and FAB-250 free-fall bombs; and rocket pods. One 30 mm Gryazev/Shipunov GSh-301 (TKB-687/9A4071K) single barrel gun in port wingroot leading-edge extension, with 150 AO-18 rounds.

DIMENSIONS, EXTERNAL:

• Wing span: 11.99 m (39 ft 4 in)
• Wing aspect ratio: 3.4
• Length overall: incl noseprobe: 17.37 m (56 ft 11¾ in)
• folded: 14.13 m (46 ft 4¼ in)
• Height overall: 5.18 m (17 ft 0 in)

AREAS:

• Wings, gross: 42.00 m² (452.1 sq ft)

WEIGHTS AND LOADINGS:

• Max weapon load: 4,500 kg (9,921 lb)
• Max fuel load: 5,240 kg (11,552 lb)
• T-O weight: normal: 18,550 kg (40,895 lb)
• max: 22,400 kg (49,383 lb)
• Max wing loading: 533.3 kg/m² (109.24 lb/sq ft)
• Max power loading: 131 kg/kN (1.29 lb/lb st)

PERFORMANCE:

• Max level speed:
• at height: 1,296 kt (2,400 km/h; 1,491 mph)
• at S/L: 670 kt (1,240 km/h; 771 mph)
• Max rate of climb at S/L: 17,760 m (58,260 ft)/min
• Service ceiling: 17,500 m (57,420 ft)
• Range:
• combat (with max internal fuel): 459 n miles (850 km; 528 miles)
• combat (with external tank): 702 n miles (1,300 km; 807 miles)
• ferry: 1,889 n miles (3,500 km; 2,174 miles)
• g limits: +8

The article appears in the following publication:
Jane's All the World's Aircraft 2007-2008. Jane's Information Group Ltd. 2007. ISBN: 0-7106-2792-0