Lavochkin La-190 1951
Owing little or nothing to earlier fighters from the Lavochkin design bureau, the La-190 was conceived to meet the demand of Yosif Stalin for the "fastest fighter in the world''. Other contenders were the I-350, progenitor of the MiG-19, and the Yak-1000, which, in the event, was to be abandoned before flight testing. The requirement called for use of the new Lyulka AL-5 turbojet which had an initial rating of 4600kg. The La-190 featured a tapered wing sweptback 55° at the leading edge, bicycle-type main undercarriage members with wingtip outrigger stabilising wheels, and an armament of two 37mm N-37 cannon. Innovations insofar as Soviet design was concerned included integral fuel tankage occupying virtually the entire interspar box of the 6.1% thickness wing which featured machined upper and lower skins. All control surfaces were powered by irreversible actuators. The sole prototype La-190 was completed in February 1951. The AL-5 engine offered less thrust than predicted and its unreliability led to cancellation of the development programme after only eight flights. However, a speed of 1190km/h at 5000m, or Mach=1.03, was attained in level flight during one test in March 1951.
Specification
WEIGHTS
Take-off weight 9257 kg 20408 lb
Empty weight 7315 kg 16127 lb
DIMENSIONS
Wingspan 9.90 m 32 ft 6 in
Length 16.35 m 53 ft 8 in
Wing area 38.93 m2 419.04 sq ft
PERFORMANCE
Max. speed 1190 km/h 739 mph
Range 1150 km 715 miles
Lavochkin La-200B 1952
The issue in November 1951 of a specification for an all-weather fighter capable of mounting standing patrols led the Lavochkin bureau to undertake some redesign of the La-200. The side-by-side seating for the two crew members was retained, and the centre and aft fuselage were comparatively unchanged, but the forward fuselage was entirely redesigned. The extreme nose was formed by a large dielectric radome of more than 1.0m diameter. The early single-antenna Torii-A radar was replaced by a large RP-6 Sokol (Falcon) radar with three different scan modes, and twin ventral strakes supplanted the single strake of the second La-200. The additional fuel required to achieve the specified endurance was provided by increasing the capacity of each underwing tank from 1120 l to 2650 l. Two 3100kg Klimov VK-1 turbojets were installed, the forward engine's air being supplied through a chin intake and that for the aft engine being provided by "elephant ear" type intakes on the sides of the extended nose. Armament remained three 37mm cannon and the first flight test was made on 3 July 1952, a mock-up of the Sokol radar initially being fitted, tests with the radar installed commencing on 10 September. An extensive test programme was conducted, but, in the event, the competitive Yak-120 was selected to fulfil the requirement
Specification
WEIGHTS
Take-off weight 12700 kg 27999 lb
Empty weight 8810 kg 19423 lb
DIMENSIONS
Wingspan 12.96 m 42 ft 6 in
Length 17.32 m 56 ft 10 in
Wing area 40.00 m2 430.56 sq ft
PERFORMANCE
Max. speed 1030 km/h 640 mph
Range 2800 km 1740 miles
Lavochkin La-250 1956
Destined to be the last aircraft produced by the Lavochkin design bureau, the La-250, known unofficially as the Anaconda, was designed to meet a very demanding 1954 requirement for an ultra long-range, high-altitude single-seat super interceptor armed exclusively with missiles. Featuring a 57° delta wing and an enormous fuselage of near-constant cross section, the La-250 was powered by two Lyulka AL-7F turbojets each rated at 6500kg which were later to be fitted with afterburners boosting thrust to 9000kg. All control surfaces were fully powered with duplex systems and without manual reversion. Intended to carry the 30km acquisition- range Uragan (Hurricane) radar, the La-250 had a planned armament of two large K-15 beam-riding missiles.
Although the La-250 was intended as a single-seater in operational form, prototypes were completed as two-seaters to provide accommodation for a test observer, and the first of three flying examples was completed in July 1956. The first flight was attempted on 16 July, but the test pilot, A G Kochetkov, encountered an unexpectedly rapid roll moment and lost control. Extensive testing of a systems rig followed before acceptable characteristics were attained and flight testing could be resumed. The second aircraft was lost in a landing accident on 28 November 1957, and the third aircraft also suffered a landing accident on 8 September 1958. The flight test programme suffered continual delays as a result of poor engine reliability and the full testing had not been completed when the programme was cancelled.
Specification
WEIGHTS
Take-off weight 30000 kg 66139 lb
Empty weight 15000 kg 33070 lb
DIMENSIONS
Wingspan 13.90 m 45 ft 7 in
Length 25.60 m 83 ft 12 in
Wing area 80.0 m2 861.11 sq ft
PERFORMANCE
Max. speed 2000 km/h 1243 mph
Ceiling 18000 m 59050 ft
Range 2000 km 1243 miles
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