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IWiG-21US / 7///Б8 / Ye-33 / Ye-ББВ
The MiG-21US two-seat training aircraft was derived from the MiG-21 U and differed externally in two points: the chord of the tail fin was broader, and the parachute container was located at the base of that fin. However, the most significant modifications were inside the aircraft. It was powered by the R-11F2S-300 turbojet rated at 6,050 daN (6,175 kg st) and consequently had the SPS system. Because the cone had no radar to house, there was no need to increase the diameter of the air intake, so the diameter remained at 690 mrn (27.2 inches). The total capacity of the fuel tanks increased to 2,4501 (647 US gallons) and
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The MiG-21 US differed from the MiG-21U in two particulars it had a broader-chord tail fin, and the tail chute canister was moved to the base of the vertical tail surfaces |
the SK ejection seats were replaced by the KM-1M (SK-3) model The MiG-21 US was mass-produced for the VVS and for export in the Tbilisi factoiy between 1966 and 1970
A M1G-21US also renamed Ye-33 and piloted by S Ye, Savitskaya broke four female world records on 6 June 1974
1 Time to climb to 3,000 m (9,840 feet), 59,1 seconds
2 Time to climb to 6,000 m (19,680 feet), 1 minute, 20.4 seconds
3, Time to climb to 9,000 m (29,520 feet), 1 minute, 46.7 seconds
4. Time to climb to 12,000 m (39,360 feet), 2 minute, 35.1 seconds
Another MiG-21US renamed Ye-66B and piloted once more by S Ye. Savitskaya topped those four records comfortably on 15 November 1974. [6] 2 [7] [8]
In the documents sent to the FAI to verify those records, it was mentioned that the Ye-66B was powered by one RDM at 6,860 daN (7,000 kg st) and two TTRDs at 2,250 daN (2,300 kg st). Those mysterious acronyms had to be deciphered; it was surmised that the RDM was in fact the R-11F2S-300 turbojet (somewhat revved up by toying with the engine combustion temperature and rotation speed) and that the TTRDs were two SPRD-99 solid rocket boosters for help at takeoff.
Specifications
Span, 7.154 m (23 ft 5.7 in); fuselage length (except cone and probe),
12.18 m (39 ft 11.5 in); wheel track, 2.692 m (8 ft 10 in); wheel base,
4.806 m (15 ft 9.2 in); wing area, 23 m[9] [10] (247.6 sq ft); takeoff weight, 8,000 kg (17,630 lb); fuel, 2,030 kg (4,475 lb); wing loading, 347.8 kg/m2 (71.3 Ib/sq ft); max operating limit load factor, 7.
Performance
Max speed, 2,175 km/h at 13,000 m (1,175 kt at 42,640 ft); max speed at sea level, 1,150 km/h (621 kt); climb rate at sea level (half internal fuel, full thrust) with two R-3S missiles, 115 m/sec (22,640 ft/min); climb to 17,200 m (56,415 ft) in 8 min; service ceiling, 17,700 m (58,055 ft); landing speed, 250-260 km/h (135-140 kt); range, 1,210 km at 14,000 m (750 mi at 45,920 ft), with 800-1 (211-US gal) drop tank, 1,460 km (905 mi); takeoff roll, 900 m (2,950 ft); landing roll with SPS and tail chute, 550 m (1,800 ft).