Lavochkin aircraft

[JG52Uther]

Lavochkin La-174TK 1948

Whereas sweptback surfaces had been adopted for both the La-168 and La-172, the La-174TK, designed to meet the demands of the same specification as the latter, featured unswept surfaces. The wing possessed a thickness ratio of only 6% (the "TK" suffix indicating Tonkoye Krylo, or Thin Wing) which the Lavochkin bureau believed might offer most of the advantages of a thicker sweptback wing while avoiding some of its disadvantages. The basic configuration of the La-174TK reverted to that of the earlier La-152 series fighters, although the relationship was confined to a common design origin, with the single 1590kg NII-1 (RD-500) turbojet exhausting under the rear fuselage. Armament comprised three 23mm NS-23 cannon and flight testing commenced early 1948. Although lighter than the La-172, the La-174TK demonstrated inferior handling and performance characteristics, further development being discontinued. The design bureau designation was reassigned to the replacement prototype for the La-172 which became the La-174D.

Specification
WEIGHTS
Take-off weight 3315 kg 7308 lb
Empty weight 2310 kg 5093 lb
DIMENSIONS
Wingspan 8.64 m 28 ft 4 in
Length 9.41 m 30 ft 10 in
Wing area 13.52 m2 145.53 sq ft
PERFORMANCE
Max. speed 970 km/h 603 mph
Range 960 km 597 miles

Lavochkin La-176 1948

Combining a fuselage essentially similar to that of the Lavochkin La-168 with wings sweptback 45° at quarter-chord, the La-176 was flown in September 1948 with a 2270kg RD-45F turbojet, and armament comprising one 37mm N-37 and two 23mm NS-23 cannon. Re-engined with a Klimov VK-1 turbojet of 2700kg, the La-176 was claimed to have exceeded Mach=1.0 in a dive from 9050m to 6000m on 26 December 1948. It was initially believed that an ASI error had been involved, but the process was repeated six times during January 1949, 1105km/h being recorded at 7500m, this being equivalent to Mach=1.02. The La-176 thus became the first Soviet aircraft to achieve supersonic flight. Further development was abandoned shortly afterwards when the canopy locks failed at high speed, resulting in test pilot Î V Sokolovsky losing his life.

Specification
WEIGHTS
Take-off weight 4631 kg 10210 lb
Empty weight 3111 kg 6859 lb
DIMENSIONS
Wingspan 8.59 m 28 ft 2 in
Length 10.97 m 35 ft 12 in
Wing area 18.25 m2 196.44 sq ft
PERFORMANCE
Max. speed 1043 km/h 648 mph
Range 1000 km 621 miles

Lavochkin La-200 1949

Designed to meet a requirement formulated in 1948 for a two-seat twin-engined all-weather interceptor, the La-200 was flown for the first time on 9 September 1949. Two prototypes were built, each powered by two 2700kg Klimov VK-1 turbojets mounted in tandem with the exhaust of the foremost engine ducted beneath the fuselage. The prototypes differed one from the other primarily in the location of the Torii (Thorium) AI radar, the first prototype having a conical intake centrebody and the second prototype having a radome underslung on the upper intake lip. Armament consisted of three 37mm N-37 cannon, one to port and two to starboard. The wing, sweptback 40° at the leading edge, was largely occupied by integral tankage and two large underwing slipper-type auxiliary tanks could boost maximum range from 1165 to 2000km.

The first prototype was flown on 9 September 1949, and the first and second flight test phases were completed by February and October 1950 respectively, Mach=0.946 being attained in level flight and Mach=1.01 in a dive. The second prototype joined the flight programme early 1951, the repositioned radar being of the improved Torii-A type, ammunition capacity being increased, a ventral keel being introduced and normal loaded weight rising to 10580kg. With the final NII VVS test phase completed in April 1951, a recommendation was made that series production of the La-200 should be initiated. This was thwarted, however, by the issue of a replacement specification in November 1951 calling for a substantial increase in range to permit all-weather standing patrols, and for the provision of heavier, longer-ranging radar. Further work on the La-200 was therefore discontinued in favour of the revised La-200B.

Specification
MODEL La-200 (1st prototype)
WEIGHTS
Take-off weight 10375 kg 22873 lb
Empty weight 7090 kg 15631 lb
DIMENSIONS
Wingspan 12.92 m 42 ft 5 in
Length 16.59 m 54 ft 5 in
Wing area 40.18 m2 432.49 sq ft
PERFORMANCE
Max. speed 1090 km/h 677 mph
Range 1165 km 724 miles

[JG52Uther]

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

[LEXX]

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