JG52Uther
12-22-2007, 11:55 AM
Lavochkin/Gorbunov/Gudkov LaGG-1 1940
Semyon A Lavochkin, together with V P Gorbunov and M I Gudkov, established a new design bureau in September 1938, and began work on a single-seat tactical fighter. Initially designated I-22, the fighter was novel in that plastic-impregnated wood known as delta drevesina was used extensively in its construction, with stressed bakelite plywood skinning. Power was provided by a 1,100hp Klimov M-105P engine with a 23mm VYa-23V cannon mounted between the cylinder banks, the remaining armament comprising two 12.7mm UB machine guns in the forward upper decking. Work began simultaneously on seven prototypes, and a preseries of 100 fighters was laid down. The first prototype was flown on 30 March 1940, the designation having meanwhile been changed to LaGG-1. It demonstrated inadequate range, ceiling and manoeuvrability, and potentially dangerous handling characteristics. The exigencies of the times did not permit fundamental redesign of the fighter, and the Lavochkin team therefore initiated a programme aimed at alleviating the more serious of the fighter's defects. Improvements were progressively introduced, while the design was subjected to a thoroughgoing weight analysis. The large calibre machine guns were replaced by 7.62mm ShKAS guns, and the 23mm cannon gave place to one of 20mm. Various palliatives for the handling shortcomings were applied, and the first LaGG-1 prototype to introduce these changes was referred to as the I-301 (from the numerical designation of the factory - GAZ-301). This also featured redesigned outer wing panels incorporating additional fuel tanks. The I-301 entered flight test on 14 June 1940, the modified aircraft being assigned the designation LaGG-3 and most pre-series examples of the LaGG-1 being completed to the later standard.
Specification
WEIGHTS
Take-off weight 3380 kg 7452 lb
Empty weight 2968 kg 6543 lb
DIMENSIONS
Wingspan 9.80 m 32 ft 2 in
Length 8.81 m 28 ft 11 in
Height 4.40 m 14 ft 5 in
Wing area 17.50 m2 188.37 sq ft
PERFORMANCE
Max. speed 600 km/h 373 mph
Range 660 km 410 miles
Lavochkin/Gorbunov/Gudkov LaGG-3 1940
The LaGG-3 was essentially the series production version of the LaGG-1 with a revised outer wing incorporating fuel tanks, and an armament of one 20mm and two 7.62mm weapons. Fixed wing slats - later replaced by automatic slats - were introduced and balance weights were added on the elevators and rudder, but were later discarded in favour of statically and dynamically balanced surfaces. Weight was reduced as a result of a structural analysis. LaGG-3 deliveries commenced in the spring of 1941, initially with the M-105P engine, but, from late in the year, with the M-105PF affording 1260hp at 800m. Provision was later made to replace one or both machine guns by weapons of 12.7mm calibre, the 20mm hub-mounted cannon being replaced by one of 23mm calibre in some cases, and a pair of 12.7mm underwing guns was sometimes fitted. Three aircraft were each fitted with a 37mm cannon and referred to as LaGG-3K-37s, and one example was fitted with the 1650hp Klimov M-107A engine. Production of the LaGG-3 was completed in the late summer of 1942 with a total of 6,528 built.
Specification
WEIGHTS
Take-off weight 3190 kg 7033 lb
Empty weight 2620 kg 5776 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.9 m 29 ft 2 in
Wing area 17.5 m2 188.37 sq ft
PERFORMANCE
Max. speed 570 km/h 354 mph
Cruise speed 450 km/h 280 mph
Ceiling 9700 m 31800 ft
Range 800 km 497 miles
Lavochkin La-5 1942
Adaptation of the basic LaGG-3 airframe for a 14- cylinder two-row radial Shvetsov M-82 engine without major redesign of fundamental components resulted in the La-5 (examples converted from existing LaGG-3 airframes on the production line sometimes being referred to as LaG-5s). The prototype conversion was first flown in March 1942 with an M-82 rated at 1700hp for take-off, and the La-5 was cleared for service testing in the following September with an armament of two 20mm cannon. With completion of the conversion of existing LaGG-3 airframes, minor changes were introduced in new production aircraft, the principal of these being the cutting down of the aft fuselage decking and the introduction of a 360°-vision canopy. Late in 1942, the improved M-82F engine became available, producing 1650hp at 1650m, aircraft fitted with this engine being designated La-5F, and, from early 1943, fuel tankage was revised. From late March 1943, the fuel injection M-82FN engine offering 1850hp for take-off replaced the carburettor-equipped M-82F, and with this power plant the fighter became the La-5FN. When the La-5 was withdrawn from production late in 1944, a total of 9,920 aircraft of this type (including La-5UTI two-seat trainers) had been built
Specification
MODEL La-5FN
WEIGHTS
Take-off weight 3360 kg 7408 lb
Empty weight 2800 kg 6173 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.60 m 28 ft 3 in
Height 2.54 m 8 ft 4 in
Wing area 17.50 m2 188.37 sq ft
PERFORMANCE
Max. speed 648 km/h 403 mph
Ceiling 11000 m 36100 ft
Range 765 km 475 miles
Lavochkin La-7 1944
The ultimate refinement of the basic La-5 rather than a new design, the La-7 was developed from the autumn of 1943 under the bureau designation of La-120. This embodied the results of a TsAGI wind tunnel programme aimed at defining areas in which the basic La-5FN could be aerodynamically improved. Incorporating the modified wing structure (metal spars replacing the wooden box spars) intended for application to the definitive La-5FN (but not to be introduced on that fighter until the late spring of 1944), a revised inboard wing leading edge and an entirely new cowling for the Shvetsov M-82FN engine, the La-120 was first flown in November 1943. In the following spring it entered production as the La-7. The intended armament comprised three 20mm Berezina B-20 cannon, but while this armament was installed in aircraft built at Yaroslavl, those built at Moscow reverted to the twin ShVAK cannon of the La-5FN. Variants included the tandem two-seat La-7UTI trainer, the La-7TK with a pair of TK-3 turbo-superchargers, and the rocket-boosted La-7R. The La-7TK was test flown in July- August 1944, but was destroyed when a turbo-supercharger exploded. Another example was fitted with the 2000hp ASh-71TK, trials soon being discontinued owing to the erratic behaviour of this engine's turbosuperchargers.
The La-7R, of which two prototypes were tested, was fitted in the rear fuselage with an RD-lKhZ liquid rocket motor of 300kg thrust, the first prototype being destroyed during the initial take-off run in October 1944. Flight testing of the second prototype continued until February 1945, and a further example - a conversion of one of the original prototype airframes and therefore referred to as the La-120R - entered test in January 1945, this having an improved rocket motor and local airframe structural changes. Testing of the La-120R continued until late 1946.
A total of 5,753 La-7s had been manufactured when production ended in 1946.
The ultimate refinement of the basic La-5 rather than a new design, the La-7 was developed from the autumn of 1943 under the bureau designation of La-120. This embodied the results of a TsAGI wind tunnel programme aimed at defining areas in which the basic La-5FN could be aerodynamically improved. Incorporating the modified wing structure (metal spars replacing the wooden box spars) intended for application to the definitive La-5FN (but not to be introduced on that fighter until the late spring of 1944), a revised inboard wing leading edge and an entirely new cowling for the Shvetsov M-82FN engine, the La-120 was first flown in November 1943. In the following spring it entered production as the La-7. The intended armament comprised three 20mm Berezina B-20 cannon, but while this armament was installed in aircraft built at Yaroslavl, those built at Moscow reverted to the twin ShVAK cannon of the La-5FN. Variants included the tandem two-seat La-7UTI trainer, the La-7TK with a pair of TK-3 turbo-superchargers, and the rocket-boosted La-7R. The La-7TK was test flown in July- August 1944, but was destroyed when a turbo-supercharger exploded. Another example was fitted with the 2000hp ASh-71TK, trials soon being discontinued owing to the erratic behaviour of this engine's turbosuperchargers.
The La-7R, of which two prototypes were tested, was fitted in the rear fuselage with an RD-lKhZ liquid rocket motor of 300kg thrust, the first prototype being destroyed during the initial take-off run in October 1944. Flight testing of the second prototype continued until February 1945, and a further example - a conversion of one of the original prototype airframes and therefore referred to as the La-120R - entered test in January 1945, this having an improved rocket motor and local airframe structural changes. Testing of the La-120R continued until late 1946.
A total of 5,753 La-7s had been manufactured when production ended in 1946.
Specification
CREW 1
WEIGHTS
Take-off weight 3400 kg 7496 lb
Empty weight 2620 kg 5776 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.6 m 28 ft 3 in
Height 2.60 m 8 ft 6 in
Wing area 17.59 m2 189.34 sq ft
PERFORMANCE
Max. speed 680 km/h 423 mph
Cruise speed 450 km/h 280 mph
Ceiling 11800 m 38700 ft
Range 990 km 615 miles
Semyon A Lavochkin, together with V P Gorbunov and M I Gudkov, established a new design bureau in September 1938, and began work on a single-seat tactical fighter. Initially designated I-22, the fighter was novel in that plastic-impregnated wood known as delta drevesina was used extensively in its construction, with stressed bakelite plywood skinning. Power was provided by a 1,100hp Klimov M-105P engine with a 23mm VYa-23V cannon mounted between the cylinder banks, the remaining armament comprising two 12.7mm UB machine guns in the forward upper decking. Work began simultaneously on seven prototypes, and a preseries of 100 fighters was laid down. The first prototype was flown on 30 March 1940, the designation having meanwhile been changed to LaGG-1. It demonstrated inadequate range, ceiling and manoeuvrability, and potentially dangerous handling characteristics. The exigencies of the times did not permit fundamental redesign of the fighter, and the Lavochkin team therefore initiated a programme aimed at alleviating the more serious of the fighter's defects. Improvements were progressively introduced, while the design was subjected to a thoroughgoing weight analysis. The large calibre machine guns were replaced by 7.62mm ShKAS guns, and the 23mm cannon gave place to one of 20mm. Various palliatives for the handling shortcomings were applied, and the first LaGG-1 prototype to introduce these changes was referred to as the I-301 (from the numerical designation of the factory - GAZ-301). This also featured redesigned outer wing panels incorporating additional fuel tanks. The I-301 entered flight test on 14 June 1940, the modified aircraft being assigned the designation LaGG-3 and most pre-series examples of the LaGG-1 being completed to the later standard.
Specification
WEIGHTS
Take-off weight 3380 kg 7452 lb
Empty weight 2968 kg 6543 lb
DIMENSIONS
Wingspan 9.80 m 32 ft 2 in
Length 8.81 m 28 ft 11 in
Height 4.40 m 14 ft 5 in
Wing area 17.50 m2 188.37 sq ft
PERFORMANCE
Max. speed 600 km/h 373 mph
Range 660 km 410 miles
Lavochkin/Gorbunov/Gudkov LaGG-3 1940
The LaGG-3 was essentially the series production version of the LaGG-1 with a revised outer wing incorporating fuel tanks, and an armament of one 20mm and two 7.62mm weapons. Fixed wing slats - later replaced by automatic slats - were introduced and balance weights were added on the elevators and rudder, but were later discarded in favour of statically and dynamically balanced surfaces. Weight was reduced as a result of a structural analysis. LaGG-3 deliveries commenced in the spring of 1941, initially with the M-105P engine, but, from late in the year, with the M-105PF affording 1260hp at 800m. Provision was later made to replace one or both machine guns by weapons of 12.7mm calibre, the 20mm hub-mounted cannon being replaced by one of 23mm calibre in some cases, and a pair of 12.7mm underwing guns was sometimes fitted. Three aircraft were each fitted with a 37mm cannon and referred to as LaGG-3K-37s, and one example was fitted with the 1650hp Klimov M-107A engine. Production of the LaGG-3 was completed in the late summer of 1942 with a total of 6,528 built.
Specification
WEIGHTS
Take-off weight 3190 kg 7033 lb
Empty weight 2620 kg 5776 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.9 m 29 ft 2 in
Wing area 17.5 m2 188.37 sq ft
PERFORMANCE
Max. speed 570 km/h 354 mph
Cruise speed 450 km/h 280 mph
Ceiling 9700 m 31800 ft
Range 800 km 497 miles
Lavochkin La-5 1942
Adaptation of the basic LaGG-3 airframe for a 14- cylinder two-row radial Shvetsov M-82 engine without major redesign of fundamental components resulted in the La-5 (examples converted from existing LaGG-3 airframes on the production line sometimes being referred to as LaG-5s). The prototype conversion was first flown in March 1942 with an M-82 rated at 1700hp for take-off, and the La-5 was cleared for service testing in the following September with an armament of two 20mm cannon. With completion of the conversion of existing LaGG-3 airframes, minor changes were introduced in new production aircraft, the principal of these being the cutting down of the aft fuselage decking and the introduction of a 360°-vision canopy. Late in 1942, the improved M-82F engine became available, producing 1650hp at 1650m, aircraft fitted with this engine being designated La-5F, and, from early 1943, fuel tankage was revised. From late March 1943, the fuel injection M-82FN engine offering 1850hp for take-off replaced the carburettor-equipped M-82F, and with this power plant the fighter became the La-5FN. When the La-5 was withdrawn from production late in 1944, a total of 9,920 aircraft of this type (including La-5UTI two-seat trainers) had been built
Specification
MODEL La-5FN
WEIGHTS
Take-off weight 3360 kg 7408 lb
Empty weight 2800 kg 6173 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.60 m 28 ft 3 in
Height 2.54 m 8 ft 4 in
Wing area 17.50 m2 188.37 sq ft
PERFORMANCE
Max. speed 648 km/h 403 mph
Ceiling 11000 m 36100 ft
Range 765 km 475 miles
Lavochkin La-7 1944
The ultimate refinement of the basic La-5 rather than a new design, the La-7 was developed from the autumn of 1943 under the bureau designation of La-120. This embodied the results of a TsAGI wind tunnel programme aimed at defining areas in which the basic La-5FN could be aerodynamically improved. Incorporating the modified wing structure (metal spars replacing the wooden box spars) intended for application to the definitive La-5FN (but not to be introduced on that fighter until the late spring of 1944), a revised inboard wing leading edge and an entirely new cowling for the Shvetsov M-82FN engine, the La-120 was first flown in November 1943. In the following spring it entered production as the La-7. The intended armament comprised three 20mm Berezina B-20 cannon, but while this armament was installed in aircraft built at Yaroslavl, those built at Moscow reverted to the twin ShVAK cannon of the La-5FN. Variants included the tandem two-seat La-7UTI trainer, the La-7TK with a pair of TK-3 turbo-superchargers, and the rocket-boosted La-7R. The La-7TK was test flown in July- August 1944, but was destroyed when a turbo-supercharger exploded. Another example was fitted with the 2000hp ASh-71TK, trials soon being discontinued owing to the erratic behaviour of this engine's turbosuperchargers.
The La-7R, of which two prototypes were tested, was fitted in the rear fuselage with an RD-lKhZ liquid rocket motor of 300kg thrust, the first prototype being destroyed during the initial take-off run in October 1944. Flight testing of the second prototype continued until February 1945, and a further example - a conversion of one of the original prototype airframes and therefore referred to as the La-120R - entered test in January 1945, this having an improved rocket motor and local airframe structural changes. Testing of the La-120R continued until late 1946.
A total of 5,753 La-7s had been manufactured when production ended in 1946.
The ultimate refinement of the basic La-5 rather than a new design, the La-7 was developed from the autumn of 1943 under the bureau designation of La-120. This embodied the results of a TsAGI wind tunnel programme aimed at defining areas in which the basic La-5FN could be aerodynamically improved. Incorporating the modified wing structure (metal spars replacing the wooden box spars) intended for application to the definitive La-5FN (but not to be introduced on that fighter until the late spring of 1944), a revised inboard wing leading edge and an entirely new cowling for the Shvetsov M-82FN engine, the La-120 was first flown in November 1943. In the following spring it entered production as the La-7. The intended armament comprised three 20mm Berezina B-20 cannon, but while this armament was installed in aircraft built at Yaroslavl, those built at Moscow reverted to the twin ShVAK cannon of the La-5FN. Variants included the tandem two-seat La-7UTI trainer, the La-7TK with a pair of TK-3 turbo-superchargers, and the rocket-boosted La-7R. The La-7TK was test flown in July- August 1944, but was destroyed when a turbo-supercharger exploded. Another example was fitted with the 2000hp ASh-71TK, trials soon being discontinued owing to the erratic behaviour of this engine's turbosuperchargers.
The La-7R, of which two prototypes were tested, was fitted in the rear fuselage with an RD-lKhZ liquid rocket motor of 300kg thrust, the first prototype being destroyed during the initial take-off run in October 1944. Flight testing of the second prototype continued until February 1945, and a further example - a conversion of one of the original prototype airframes and therefore referred to as the La-120R - entered test in January 1945, this having an improved rocket motor and local airframe structural changes. Testing of the La-120R continued until late 1946.
A total of 5,753 La-7s had been manufactured when production ended in 1946.
Specification
CREW 1
WEIGHTS
Take-off weight 3400 kg 7496 lb
Empty weight 2620 kg 5776 lb
DIMENSIONS
Wingspan 9.8 m 32 ft 2 in
Length 8.6 m 28 ft 3 in
Height 2.60 m 8 ft 6 in
Wing area 17.59 m2 189.34 sq ft
PERFORMANCE
Max. speed 680 km/h 423 mph
Cruise speed 450 km/h 280 mph
Ceiling 11800 m 38700 ft
Range 990 km 615 miles