TITLE:
MIKOYAN MiG-29
NATO reporting name: Fulcrum
Indian Air Force name: Baaz (Eagle)
TYPE:
All-weather single-seat counter-air fighter with attack capability, and two-seat combat trainer.
PROGRAMME:
Technical assignment (operational requirement) issued 1972, to replace MiG-21, MiG-23, Su-15 and Su-17; initial order placed simultaneously; detail design began 1974; first of 14 prototypes built for factory and State testing flew 6 October 1977; photographed by US satellite, Ramenskoye flight test centre, November 1977 and given interim Western designation 'Ram-L'; second prototype flew June 1978; second and fourth prototypes lost through engine failures; after major design changes (see previous editions of Jane's) production began 1982, deliveries to Frontal Aviation 1984; operational early 1985; first detailed Western study possible after visit of demonstration team to Finland July 1986; production of basic MiG-29 combat aircraft by Moscow Aircraft Production Group (MAPO), and of MiG-29UB combat trainers at Nizhny Novgorod, for CIS air forces completed, but manufacture for export continues.
DESIGN FEATURES:
All-swept low-wing configuration, with wide ogival wing leading-edge root extensions (LERX), lift-generating fuselage, twin tail fins carried on booms outboard of widely spaced engines with wedge intakes; doors in intakes, actuated by extension and compression of nosewheel leg, prevent ingestion of foreign objects during take-off and landing; gap between roof of each intake and skin of wingroot extension for boundary layer bleed; fire control and mission computers link radar with laser rangefinder and infrared search/track sensor, in conjunction with helmet-mounted target designator; radar able to track 10 targets simultaneously; targets can be approached and engaged without emission of detectable radar or radio signals; sustained turn rate much improved over earlier Soviet fighters; thrust/weight ratio better than one; allowable angles of attack at least 70 per cent higher than previous fighters; difficult to get into stable flat spin, reluctant to enter normal spin, recovers as soon as controls released; wing leading-edge sweepback 73 degrees 30' on LERX, 42 degrees on outer panels; anhedral approx 2 degrees; tail fins canted outward 6 degrees; leading-edge sweep 47 degrees 50' on fins, approx 50 degrees on horizontal surfaces. Design flying life 2500 h.
STRUCTURE:
Approx 7 per cent of airframe, by weight, of composites; remainder metal, including aluminium-lithium alloys; trailing-edge wing flaps, ailerons and vertical tail surfaces of carbonfibre honeycomb; approx 65 per cent of horizontal tail surfaces aluminium alloy, remainder carbonfibre; semi-monocoque all-metal fuselage, sharply tapered and downswept aft of flat-sided cockpit area, with ogival dielectric nosecone; small vortex generator each side of nose helps to overcome early tendency to aileron reversal at angles of attack above 25 degrees; tail surfaces carried on slim booms alongside engine nacelles.
LANDING GEAR:
Retractable tricycle type, made by Hydromash, with single wheel on each main unit and twin nosewheels. Mainwheels retract forward into wingroots, turning through 90 degrees to lie flat above leg; nosewheels, on trailing-link oleo, retract rearward between engine air intakes. Hydraulic retraction and extension, with mechanical emergency release. Nosewheels steerable +/-8 degrees for taxiing, T-O and landings, +/-30 degrees for slow speed manoeuvring in confined areas (selector in cockpit).
POWER PLANT:
Two Klimov/Sarkisov RD-33 turbofans, each 49.4 kN (11,110 lb st) dry and 54.9-81.4 kN (12,345-18,300 lb st) with afterburning. Engine ducts canted at approx 9 degrees, with wedge intakes, sweptback at approx 35 degrees, under wingroot leading-edge extensions. Multi-segment ramp system, including top-hinged forward door (containing a very large number of small holes) inside each intake that closes the duct while aircraft is taking off or landing, to prevent ingestion of foreign objects, ice or snow. Air is then fed to each engine through louvres in top of wingroot leading-edge extension and perforations in duct closure door. Basic 'Fulcrum-A' has four integral fuel tanks in inboard portion of each wing and in fuselage between wings; total capacity 4365 litres (1153 US gallons; 960 Imp gallons).
ACCOMMODATION:
Pilot only, on 10 degrees inclined K-36DM zero/zero ejection seat, under rearward hinged transparent blister canopy in high-set cockpit. Sharply inclined one-piece curved windscreen. Three internal mirrors provide rearward view.
AVIONICS:
RP-29 (N019 Sapfir-29) coherent pulse Doppler lookdown/shootdown engagement radar (NATO 'Slot Back'; search range 54 nm; 100 km; 62 miles, tracking range 38 nm; 70 km; 43 miles), target tracking limits 60 degrees up, 38 degrees down, 67 degrees each side, collimated with laser rangefinder; infrared search/track sensor (fighter detection range 8 nm; 15 km; 9.25 miles) forward of windscreen (protected by removable fairing on non-operational flights); R-862 com radio; ARK-19 DF; inertial navigation system; SRO-2 (NATO 'Odd Rods') IFF transponder and SRZ-15 interrogator; Sirena-3 360 degrees radar warning system, with sensors on wingroot extensions, wingtips and port fin. Two SO-69 ECM antennae under conformal dielectric fairings in leading-edge of each wingroot extension; head-up display; and helmet-mounted target designation system for off-axis aiming of air-to-air missiles.
ARMAMENT:
Six close-range R-60MK (NATO AA-8 'Aphid') infrared air-to-air missiles, or four R-60MK and two medium-range radar guided R-27R1 (AA-10A 'Alamo-A'), on three pylons under each wing; alternative air combat weapons include R-73E (AA-11 'Archer') close-range infrared missiles. Able to carry FAB-250 bombs, KMGU-2 submunitions dispensers, 3B-500 napalm tanks, and 80 mm, 130 mm and 240 mm rockets in attack role. One 30 mm GSh-301 gun in port wingroot leading-edge extension, with 150 rds.
DIMENSIONS: EXTERNAL:
Wingspan: 11.36 m (37 ft 3{1/4} in)
Wing chord: at c/l: 5.60 m (18 ft 4{1/2} in)
at tip: 1.27 m (4 ft 2 in)
Wing aspect ratio: 3.5
Length overall: incl noseprobe: 17.32 m (56 ft 10 in)
excl noseprobe: 16.28 m (53 ft 5 in)
Height overall: 4.73 m (15 ft 6{1/4} in)
Tailplane span: 7.78 m (25 ft 6{1/4} in)
WEIGHTS AND LOADINGS:
Operating weight empty: 10,900 kg (24,030 lb)
Max weapon load: 3000 kg (6615 lb)
Max fuel load: 4640 kg (10,230 lb)
Normal T-O weight (interceptor): 15,240 kg (33,600 lb)
Max T-O weight: 18,500 kg (40,785 lb)
Max wing loading: 486.8 kg/m{2} (99.7 lb/sq ft)
Max power loading: 113.6 kg/kN (1.11 lb/lb st)
PERFORMANCE:
Max level speed:
at height: Mach 2.3 (1320 knots; 2445 km/h; 1520 mph)
at S/L: Mach 1.06 (700 knots; 1300 km/h; 805 mph)
Max rate of climb at S/L: 19,800 m (65,000 ft)/min
Service ceiling: 17,000 m (55,775 ft)
Range:
with max internal fuel: 810 nm (1500 km; 932 miles)
with underbelly auxiliary tank:
1133 nm (2100 km; 1305 miles)
g limits: above Mach 0.85: +7
below Mach 0.85: +9
LENGTH (m): 17.32
HEIGHT (m): 4.73
WINGSPAN (m): 11.36
MAX T-O WEIGHT (kg): 18,500
MAX WING LOAD (kg/m{2}): 486.80
MAX LEVEL SPEED (knots): 700
MAX RANGE (nm): 1133
T-O RUN (m): 250
LANDING RUN (m): 600
MAX RATE CLIMB (m/min): 19,800
SERVICE CEILING (m): 17,000
