Other designations or related variants include—I, MiG-23B, MIG-23BM, MiG-23BN, MiG-23DPD, MiG-23M, MiG-23MF, MiG-23ML, MiG-23MLD, MiG-23MS, MiG-23S, MiG-23SM, MiG-23U, MiG-23UB, MiG-23UM, MiG-27, MIG-27D, MiG-27K, MiG-27M, product 23-11, product 23-16, product 32-24, product 32-25, Ye-23, Ye-230, Ye-231.
Production/Prototype Quantities—Nearly 4,500 delivered. Production now has ended.
Cockpit—Single KM-1M zero-zero ejection-seat in single-seat interceptor versions and ground attack versions. Trainers have two KM-1Ms and extended canopy transparencies w/dual upward hinged segments. Cockpit is fully pressurized and air-conditioned. Canopy for single-seat aircraft consists of single-piece unit hinged at the rear w/hydraulic actuation. Forward windscreen is three-transparency design and is effectively bullet-proof. Conventional stick and rudder controls. Instrumentation is totally analogue w/some vertical displays. Hooded radar screen mounted off-center on right. Late-model aircraft have panels w/some digital displays and CRTs to accommodate various weapon system controls. Some aircraft also have small, electrically-heated rearview mirror mounted in canopy top center. Other equipment includes an R-832M UHF radio, a SOD-57M transponder, a Syrena-3 radar warning system, a Chrom-Nikiel IFF. an ARK-15M automatic radio compass, an RV-4 radio altimeter, and MRP-56P marker beacon receiver, and an RSBN-6S navigation approach and landing system.
Fuselage—Two-section (aft section beginning at fuselage rib 28 removable for powerplant access) semi-monococque design of primarily aluminum construction. Essentially circular cross-section w/intakes representing rectangular side elements. Area of fuselage ahead of intake is flattened to accommodate flow distortion requirements at high speed. This design element is somewhat more exaggerated in the MiG-27 series. MiG-23 variants are equipped w/variablе-position ramp splitter plates and MiG-27 variants are equipped w/smaller, fixed-geometry surfaces optimized for boundary layer flow control. Intake cheeks are equipped w/blow-in doors to improve intake mass flow during taxi or in low-speed flight. Further aft and located ventrally under fuselage behind main gear wells are pressure relief vents. Just forward of the exhaust fairing on the empennage are four (two per side) hydraulically-actuated airbrakes. MiG-23B/BN and MiG-27 incorporate a redesigned nose w/heavy emphasis being placed on the view forward from the cockpit (thus extreme slope) and increased armor plate for protection against ground fire.
Lifting and Control Surfaces—Variable-geometry wings of cantilever, shoulder-position design w/leading edge dogtooth. Movable outboard surfaces have two main spars and a single auxiliary spar—all attached to a single pivot-type hinge. Sweep back is manually controlled by the SPK-1 system through pilot commands and has three pre-selected positions (16o, 45o, and 72o). The actuation system is hydro-mechanical via two hydraulic units driven separately by a primary and back-up system. Use of back-up system only increases actuation time by half. Four-section leading edge flaps occupying outer two-thirds of movable wing surface and interfaced w/trailing edge flaps are hydraulically actuated and extend downward a max. of 20o. Three-section trailing edge single-slotted flaps allow outboard sections to be utilized even when wing is fully swept. There are no ailerons as roll control is via two-section, hydraulically-actuated spoilers (w/max. extension angle of 45o) and all-moving slab stabilators. Spoilers are inactivated, however, when wing is fully swept. Spoilers can also be utilized to destroy lift during landing. Spoilers are located aft of mid- and inner-flap segments. Inboard fixed center section is glove unit housing sweep mechanisms and welded steel pivot box and associated carry-through structure. Construction materials of main wing surface and spar assemblies are conventional aluminum alloys w/steel. Vertical and horizontal tail surfaces are of conventional aluminum construction. Vertical tail has a leading edge sweep angle of 65o and a single-piece hydraulically-actuated rudder. The hydraulically-actuated slab-type, all-moving horizontal stabilators have а 57o leading edge sweep angle and are designed to work symmetrically for pitch control and differentially for roll. Rudder and rear section of each stabilator are aluminum w/honeycomb core. Some later variants are equipped w/ground-adjustable trim tabs. A folding (w/fold to the right) ventral fin accommodates directional stability requirements at high a.o.a. The told sequence is coordinated hydro-mechanically w/the retraction and extension of the landing gear and thus provides sufficient ground clearance for landing and takeoff rotation.
Landing Gear—The MiG-23 and MiG-27 are equipped w/an unusual hydraulically-actuated tricycle landing gear. The retraction sequence is practical, but somewhat complex for main gear, as the system requires several pivot assemblies in order to retract it into its respective wells. The system, however, provides suitable wheel track and tread dimensions while utilizing minimal fuselage interior volume. The main gear tires are relatively low-pressure tubeless types w/a size of 33 in. by 11.4 in. (840 mm. by 290 mm.). The nose landing gear is equipped w/dual low-pressure tubeless tires w/a size of 20.5 in. by 4.9 in. (520 mm. by 125 mm.). The nose gear also is equipped w/a mud-guard assembly to keep rough field operations from causing unwanted foreign matter from entering the wheel well or the engine intakes. All wheels are equipped w/disc-type brakes and an associated anti-skid system. The wheel wells are all fully enclosed: the nose gear has two conventional doors w/mechanical linkages which are synchronized to function w/the gear strut assembly as it retracts; and the main gear are equipped w/two-part doors that are similarly mechanically actuated but which are split w/one door section attached to the gear lower strut segment and one attached to the fuselage. The wheel track is 9 ft. 2 in. (2.85 m.) and the wheel base dimension is 18 ft. 7 in. (5.812 m.). A drag chute compartment in the form of a bullet fairing at the base of the vertical fin contains a double canopy nylon drag chute w/an area of 226 ft.2 (21 m.2).
Miscellaneous Equipment—The various radar systems utilized by MiG-23s are as follows: MiG-23MS uses NATO Jaybird w/pulse search-and-track capability, and multiple threat indicator; MiG-23M/MiG-23MF uses NATO High Lark w/puise search-and-track capability, and multiple threat indicator; MiG-23ML uses NATO High Lark II w/pulse search-and-track capability, and multiple threat indicator; MiG-23 uses NATO High Lark II w/pulse search-and-track capability and multiple threat indicator; MIG-23B/MiG-23BN uses NATO High Fix w/air-to-ground and air-to-air ranging capability only; MiG-27 uses NATO High Fix w/air-to-ground and air-to-air ranging capability only; MIG-27M uses NATO High Fix w/air-to-ground and air-to-air ranging capability only. High Lark radar systems reportedly have a search range of approx. 53 mi. (85 km.) and a tracking range of 34 mi (54 km). Other systems include NATO Swift Rod ILS w/antenna mounted under nose and vertical fin tip trailing edge; a TP-23 infrared sensor unit mounted ventrally under the nose; various UHF and VHF antenna behind dielectric panels on vertical fin and ventral fin; SRO-2 (NATO Odd Rods) IFF; and a retractable taxi/landing light under each intake cheek. Ground attack variants are usually equipped w/laser range finding units in the tip of the nose and additional systems to accommodate ground attack mission requirements. Some non-indigenous aircraft have been modified to accept inflight refueling probes on the forward nose section.
Powerplant/Fuel—MiG-23B/BN is powered by one 27,558 lb. (12,500 kg.) th. Tumansky R-29-300; MiG-23S is powered by one 22,487 lb. (10,200 kg.) th. Tumansky R-27F2M-300 turbojet; MIG-23M is powered by one 27,558 lb. (12,500 kg.) th. Tumansky R-29-300 turbojet; MIG-23ML is powered by one 28,660 lb. (13,000 kg.) th. Tumansky R-35-300 turbojet; MiG-23UM is powered by one 22,487 lb. (10,200 kg.) th. Tumansky R-27F2M-300 turbojet; MiG-27M is powered by one 25,353 lb. (11,500 kg.) th. Tumansky R-29B-300 turbojet. Bifurcated intake system is equipped w/variable ramps on interceptor/fighter versions and fixed ramps on ground attack (except for MiG-23B/BN). Most MiG-23/MiG-27 variants carry a water injection system w/a capacity of 7.4 gal. (28 lit.). There are four fuselage fuel tanks mounted aft of the cockpit area, two in the inboard, fixed sections (one ea. side) of the wings, and four in the outboard sections (two ea. side). Max. internal fuel capacity is 1.517 gal. (5,750 lit.). As many as three expendable aux. fuel tanks w/a capacity of 211 gal. (800 lit.) ea. can be carried on the centerline pylon and two non-swiveling outer wing pylons Use of the latter dictate, on early model aircraft, that the wings be kept in their fully unswept position. Late model MiG-23s have articulated wing pylons to permit use of the tanks even w/the wings partially swept. RATO bottles can be utilized and are provided attachment fittings under the aft fuselage.
Armament—MiG-23 (interceptor variants)— 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 С w/radar homing); and NATO AA-11 Archer. A single GSh-23L 23 mm. cannon is mounted in a ventral bay just ahead of and between the main landing gear. The MiG-23B/BN/MiG-27 series, optimized for ground attack, carry a variety of weapons that include the UB-16, UB-32, and UB-20 rocket pods (w/sixteen or thirty-two 57 mm. S-5 or twenty 80 mm tin-guided air-to-surface rockets each), a single S-240 rocket, or a variety of conventional bombs. K-13/NATO AA-2 Atoll. R-607NATO AA-8 Aphid: and NATO AA-11 Archer air-to-air missiles remain an option. NATO AS-7 Kerry. NATO AS-10 Karen: and NATO AS-14 Kedge (normally requiring a laser guidance pod fitted to the centerline pylon) can be utilized tor ground attack against specialized targets, including radar. Various 220 lb. (100 kg.) RPK-100, 200 lb. (100 kg.) FAB 100, and 1,102 lb. (500 kg.) FAB 500 bombs, PTK 250 cluster dispensers, RPK-100 fragmentation bombs, BETA B-25 concrete piercing bombs, 1,102 lb. (500 kg.) laser-guided bombs, FAE (fuel/air explosive) bombs, and other such weapons can be carried externally. All bombs usually are carried on 2 or 4 pylon racks—w/up to 18 bombs being carried at any one time. The MiG-27 normally is equipped w/the GSh-6-N-30 30 mm. rotary-barrel cannon w/approx. 700 rds. available in an internal ammunition drum feeder unit. UPK-23 23mm gun pods. 23 mm. 15o depressed single-barrel gun pods, and TN-1000 or TN-1200 tactical nuclear weapons are optional.
Length—MiG-23S w/probe: 54 ft. 8 in. (17.05 m.); MiG-23M w/o probe: 52 ft. 5 in (16.35 m.); MiG-23M w/probe: 55 ft. 1 in. (17.18 m.); MiG-23ML w/probe: 53 ft. 7 in. (16.7 m.); MiG-23UB w/o probe: 50 ft. 8 in (15.80 m.); MiG-23UB w/probe: 53 ft. 5 in. (16.64 m.).
Wlngspan—MiG-23S at 16o: 44 ft. 3 in. (13.8 m.); MiG-23S at 72o: 23 ft 8 in. (7.4 m.); MiG-23M at 16o: 44 ft. 9 in. (13.965 m.); MIG-23M at 72o: 25 ft. 0 in. (7.779 m.); MiG-23ML at 16o: 44 ft. 9 in. (13.965 m.); MIG-23ML at 72o: 25 ft. 0 in. (7.779 m.); MiG-23UB at 16o: 44 ft. 9 in. (13.965 m.); MiG-23UB at 72o: 25 ft. 0 in. (7,779 m); MIG-27M at 16o: 44 ft. 9 in. (13.965 m.); MiG-27M at 72o: 25 ft. 0 in. (7.779 m.).
Wing area—MiG-23M at 16o: 401.45 ft.2 (37.3 m.2); MiG-23M at 72o: 368.09 ft.2 (34.2 m.2); MiG-23ML at 16o: 401.45 ft.2 (37.3 m.2); MIG-23ML at 72o: 368.09 ft.2 (34.2 m.2); MIG-23UB at 16o: 401.45 ft.2 (37.3 m.2); MiG-23UB at 72o: 368.09 ft.2 (34.2 m2).
Height—MiG 23S: 13 ft. 11 in. (4.35 m.); MiG-23M: 15 ft. 5 in.(4.82 m.); MiG-23UB: 15 ft. 5 in. (4.82 m.)
Empty weight—MiG-23: 24,251 lb. (11,000 kg.); MiG-23S: 23,589 lb. (10,700 kg.); MiG-23М: 23,909 lb. (10,845 kg.).
Gross weight-MiG-23S: 39,462 lb. (17,900 kg); MiG-23M: 39,749 lb. (18,030 kg); MiG-23ML: 39,242 lb. (17,800 kg); MlG-23UB: 37,390 lb. (16,960 kg); MiG-27M: 45,635 lb. (20,700 kg.)
Avg. combat th. to weight—MiG-23: .94: MiG-23B: .93; MiG-23BN: .83; MiG-23M: .94; MiG-23MF: .94; MIG-23ML: .94; MiG-23: .94; MC-23MS: .93; MiG-27: .86. MiG-27M: .86.
Instantaneous turn capability—MiG-23: 18o to 20o/sec.; MIG-23B: 16o to 18o/sec.; MIG-23BN: 16o to 18o/sec.; MiG-23M: 16o to 18o/sec.; MIG-23MF: 16o to 18o/sec.; MiG-23ML 18o to 20o/sec.; MiG-23MS: 18o to 20o/sec.; MiG-27: 16o to 18o/sec.; MiG-27M: 16o to 18o/sec.
Sustained turn capability—MiG-23: 8o to 10o/sec.; MiG-23B: 8o to 10o/sec.; MiG-23BN: 8o to 10o/sec.; MiG-23M: 8o to 10o/sec.; MiG-23MF: 8o to 10o/sec.; MiG-23ML: 8o to 10o/sec.; MiG-23MS: 8o to 10o/sec.; MiG-27: 6o to 8o/sec.; MiG-27M: 6o to 8o/sec.
Max. speed @ s.l. —MiG-23S: 839 mph (1,350 km/h); MiG-23М: 839 mph (1.350 km/h); MiG-23ML: 870 mph (1.400 km/h); MiG-23UB: 839 mph (1,350 km/h); MIG-27M: 839 mph (1.350 km/h).
Max. speed —MiG-23S: 1.553 mph at 35.292 ft. (2,500 km/h al 11,000 m); MiG-23M: 1.553 mph at 35.292 ft (2,500 km/h at 11.000 m); MiG-23ML: 1.553 mph at 35.292 ft. (2.500 km/h at 11,000 m); MiG-23UB: 1.553 mph at 35.292 ft. (2.500 km/h at 11.000 m); MIG-27M: 1.168 mph at 35,292 ft. (1.880 km/h at 11.000 m).
Rate of cllmb—MiG-23ML: 770 ft ./sec. (240 m./sec).
Service celling—MiG-23S: 57,750 ft. (18,000 m.): MIG-23M: 56.146 ft. (17,500 m); MiG-23UB: 55,183 ft (17,200 m.).
Max. range—MiG-23S w/aux. tanks: 1.864 mi. (3,000 km); MiG-23М w/o aux tanks: 1,181 mi (1,900 km); MiG-23M w/aux tanks: 1,740 mi (2,800 km.); MiG-23ML w/o aux tanks: 932 mi. (1,500 km); MiG-23ML w/aux tanks: 1,584 mi. (2,550 km): MiG-23UB w/o aux tanks: 1,056 mi. (1,700 km ); MiG-23UB w/aux. tanks: 1,578 mi. (2,540 km); MiG-27 w/o aux tanks: 1.087 ml. (1,750 km); MiG-27 w/aux. tanks: 1,553 mi. (2,500 km).
Notes—MiG-23L has a g-limit of 8.5. MiG-27M has a g-limit of 7.0. MiG-23M takeoff run is 1,861 ft. to 2,567 ft. (580 m. to 800 m); MiG-23ML takeoff run is 1,604 ft. (500 m.); MiG-23UB takeoff run is 2,085 ft. to 2.246 ft. (650 m. to 700 m.); MiG-27M takeoff run is 2,567 ft (800 m.). MIG-23S landing run is 2.406 ft. (750 m); MiG-23M landing run is 2.647 ft. (825 m.); MiG-23ML landing run is 2.406 ft. (750 m.); MiG-23UB landing run is 2.727 ft. (850 m); MiG-27M landing run is 3,048 ft. (950 m.).
Wlngspan—MiG-23S at 16o: 44 ft. 3 in. (13.8 m.); MiG-23S at 72o: 23 ft 8 in. (7.4 m.); MiG-23M at 16o: 44 ft. 9 in. (13.965 m.); MIG-23M at 72o: 25 ft. 0 in. (7.779 m.); MiG-23ML at 16o: 44 ft. 9 in. (13.965 m.); MIG-23ML at 72o: 25 ft. 0 in. (7.779 m.); MiG-23UB at 16o: 44 ft. 9 in. (13.965 m.); MiG-23UB at 72o: 25 ft. 0 in. (7,779 m); MIG-27M at 16o: 44 ft. 9 in. (13.965 m.); MiG-27M at 72o: 25 ft. 0 in. (7.779 m.).
Wing area—MiG-23M at 16o: 401.45 ft.2 (37.3 m.2); MiG-23M at 72o: 368.09 ft.2 (34.2 m.2); MiG-23ML at 16o: 401.45 ft.2 (37.3 m.2); MIG-23ML at 72o: 368.09 ft.2 (34.2 m.2); MIG-23UB at 16o: 401.45 ft.2 (37.3 m.2); MiG-23UB at 72o: 368.09 ft.2 (34.2 m2).
Height—MiG 23S: 13 ft. 11 in. (4.35 m.); MiG-23M: 15 ft. 5 in.(4.82 m.); MiG-23UB: 15 ft. 5 in. (4.82 m.)
Empty weight—MiG-23: 24,251 lb. (11,000 kg.); MiG-23S: 23,589 lb. (10,700 kg.); MiG-23М: 23,909 lb. (10,845 kg.).
Gross weight-MiG-23S: 39,462 lb. (17,900 kg); MiG-23M: 39,749 lb. (18,030 kg); MiG-23ML: 39,242 lb. (17,800 kg); MlG-23UB: 37,390 lb. (16,960 kg); MiG-27M: 45,635 lb. (20,700 kg.)
Avg. combat th. to weight—MiG-23: .94: MiG-23B: .93; MiG-23BN: .83; MiG-23M: .94; MiG-23MF: .94; MIG-23ML: .94; MiG-23: .94; MC-23MS: .93; MiG-27: .86. MiG-27M: .86.
Instantaneous turn capability—MiG-23: 18o to 20o/sec.; MIG-23B: 16o to 18o/sec.; MIG-23BN: 16o to 18o/sec.; MiG-23M: 16o to 18o/sec.; MIG-23MF: 16o to 18o/sec.; MiG-23ML 18o to 20o/sec.; MiG-23MS: 18o to 20o/sec.; MiG-27: 16o to 18o/sec.; MiG-27M: 16o to 18o/sec.
Sustained turn capability—MiG-23: 8o to 10o/sec.; MiG-23B: 8o to 10o/sec.; MiG-23BN: 8o to 10o/sec.; MiG-23M: 8o to 10o/sec.; MiG-23MF: 8o to 10o/sec.; MiG-23ML: 8o to 10o/sec.; MiG-23MS: 8o to 10o/sec.; MiG-27: 6o to 8o/sec.; MiG-27M: 6o to 8o/sec.
Max. speed @ s.l. —MiG-23S: 839 mph (1,350 km/h); MiG-23М: 839 mph (1.350 km/h); MiG-23ML: 870 mph (1.400 km/h); MiG-23UB: 839 mph (1,350 km/h); MIG-27M: 839 mph (1.350 km/h).
Max. speed —MiG-23S: 1.553 mph at 35.292 ft. (2,500 km/h al 11,000 m); MiG-23M: 1.553 mph at 35.292 ft (2,500 km/h at 11.000 m); MiG-23ML: 1.553 mph at 35.292 ft. (2.500 km/h at 11,000 m); MiG-23UB: 1.553 mph at 35.292 ft. (2.500 km/h at 11.000 m); MIG-27M: 1.168 mph at 35,292 ft. (1.880 km/h at 11.000 m).
Rate of cllmb—MiG-23ML: 770 ft ./sec. (240 m./sec).
Service celling—MiG-23S: 57,750 ft. (18,000 m.): MIG-23M: 56.146 ft. (17,500 m); MiG-23UB: 55,183 ft (17,200 m.).
Max. range—MiG-23S w/aux. tanks: 1.864 mi. (3,000 km); MiG-23М w/o aux tanks: 1,181 mi (1,900 km); MiG-23M w/aux tanks: 1,740 mi (2,800 km.); MiG-23ML w/o aux tanks: 932 mi. (1,500 km); MiG-23ML w/aux tanks: 1,584 mi. (2,550 km): MiG-23UB w/o aux tanks: 1,056 mi. (1,700 km ); MiG-23UB w/aux. tanks: 1,578 mi. (2,540 km); MiG-27 w/o aux tanks: 1.087 ml. (1,750 km); MiG-27 w/aux. tanks: 1,553 mi. (2,500 km).
Notes—MiG-23L has a g-limit of 8.5. MiG-27M has a g-limit of 7.0. MiG-23M takeoff run is 1,861 ft. to 2,567 ft. (580 m. to 800 m); MiG-23ML takeoff run is 1,604 ft. (500 m.); MiG-23UB takeoff run is 2,085 ft. to 2.246 ft. (650 m. to 700 m.); MiG-27M takeoff run is 2,567 ft (800 m.). MIG-23S landing run is 2.406 ft. (750 m); MiG-23M landing run is 2.647 ft. (825 m.); MiG-23ML landing run is 2.406 ft. (750 m.); MiG-23UB landing run is 2.727 ft. (850 m); MiG-27M landing run is 3,048 ft. (950 m.).
