NK-23ML/ 23-12

In the process of developing and upgrading the MiG-23 family, the MiG-23ML (rolled out in 1976) marked an important milestone that involved a complete refurbishing of the MiG-23M: a new engine, new systems, new missiles, and new radar capabilities The R-29-300 turbo­jet was replaced by a first-series Khachaturov R-35 (R-35-300) rated at 8,380 daN (8,550 kg st) dry and 12,450-12,740 daN (12,700-13,000 kg st) with throttleable afterburner Total fuel weight with three 800-1 (211-US gallon) drop tanks reached 5,500 kg (12,120 pounds)

With its more powerful engine, the M1G-23ML marked a watershed in the aircraft’s development. Armament includes two R-23 and four R-60 air-to-air missiles

The MiG-23ML differed from the MiG-23M in many other aspects as well:

—the trailing edge flaps were divided into three sections —the automatic flight control system was upgraded and renamed SAU-23AM

—the aircraft’s weight was reduced by removing the fourth fuse­lage tank

—the new Polyot ("flight”) flight management system was installed, including landing and short-range navigation systems, heading and vertical reference unit, and altitude and speed sensor; the Polyot was linked to the SAU-23M and could operate simultaneously —the forward-sector scanning and fire control system, upgraded and renamed S-23ML, featured the Sapfir-23ML radar, the TP-23M infrared sensor, and the ASP-17ML sighting system —six store points (four under the fuselage and two under the wing glove) carried the usual weaponry, including R-23R/R-23T air-to – air missiles to supplement the MiG-23M cannons and rockets — two UPK-23-250 gun pods housing GSh-23L cannons could be mounted beneath the wing

—the shape of the tail fin was modified by shortening the dorsal fin

This photograph dearly shows the shape of the type 3 wing with leading edge flaps The GSh-23L twin-barrel cannon is visible between the air intakes (Photo RR)

A MiG-23ML takes off with full reheat The undercarriage is retracting, and the ventral fin is already fully unfolded (Photo RR)

Close up of the R-35 afterburner’s flame holder rings. Foreground, the flap-type nozzle. (Photo RR)

A MiG-23ML lands in Finland with open tail chute. The new fin shape is a distinctive feature of this model. (Photo RR)

The MiG-23ML entered production in 1976 and was built until 1981. All were later upgraded to the MLD standard as quickly as they were returned to the overhaul shops. Aircraft of this type visited Fin­land and France as part of an exchange prqiect in 1978—without their IR sensor, however.

Specifications

Span (72° sweep), 7.779 m (25 ft 6.3 in); span (16° sweep), 13.965 m (45 ft 9.8 in); fuselage length (except probe), 15.65 m (51 ft 3.7 in); wheel track, 2.658 m (8 ft 8.7 in); wheel base, 5.772 m (18 ft 11.3 in); wing area (72° sweep), 34.16 m2 (367.7 sq ft); wing area (16° sweep),

37.35 m2 (402 sq ft); takeoff weight, 14,700 kg (32,400 lb); max takeoff weight, 17,800 kg (39,230 lb); wing loading (72° sweep), 430.4-521 kg/m2 (88.2-106.8 lb/sq ft); wing loading (16° sweep), 393.6-476.6 kg/m2 (80.7-97.7 lb sq ft); max operating limit load factor, 8.5 at < Mach 0.85, 7.5 at > Mach 0.85.

Performance

Max speed in clean configuration (72° sweep), 2,500 km/h or Mach

2.35 (1,350 kt); max speed in clean configuration (16° sweep), 940 km/h or Mach 0.8 (508 kt); service ceiling, 18,500 m (60,680 ft); ferry range, 1,950 km (1,210 mi); with three 800-1 (211-US gal) drop tanks, 2,820 km (1,750 mi).