Lavochkin La-150
| Lavochkin La-150 | |
|---|---|
| Type: | Fighter plane |
| Design country: | |
| Manufacturer: | |
| First flight: |
September 1946 |
| Commissioning: |
- |
| Production time: |
1946-1947 |
| Number of pieces: |
approx. 15 |
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The Lavochkin La-150 ( russian Лавочкин Ла-150 , NATO reporting name Type 3 ) was one of several jet fighter projects Lawotschkins that after the Second World War have been developed and benefited from experience with captured German technology.
development
The engine used was a Jumo 004 unit , which had been copied in the Soviet Union under the designation RD-10 . Because this was rather inefficient, the aircraft was kept light and practically constructed around the engine. The machine was first flown in September 1946 with test pilot A. A. Popow at the wheel. Five more prototypes were built to test the flight behavior of jet aircraft at high speeds. The increased occurrence of stability deficiencies during these tests led to the development of the La-150M ( La-13 ) with a modified rudder unit, a steel-clad tail unit carrier and wing tips that were pulled down by 30 °. It was the first Soviet jet aircraft to receive the RD-10F engine equipped with an afterburner . The testing took place in April 1947 by Iwan Fjodorow and Mark Gallai . She reached a top speed of 950 km / h at an altitude of 5000 meters.
Next came the La-152 , La-154 and La-156 with reinforced fuselages for experiments with different laminar airfoils. These tests were alternately completed in the summer of 1947 by the test pilots Popov, Fyodorow, Gallai. In contrast to the La-150 / La-150M, these aircraft were middle -winged . A total of about 15 La-150 to La-156 were built. Based on the results of the testing, the next decision was to develop types with swept wings, which led to the construction of the La-160 .
technical description
The La-150 / 150M was a cantilevered shoulder wing (La-152/154/56 middle wing) in all-metal construction. The fuselage had a central air inlet and was equipped with a tail unit so that the hot exhaust gases could escape undisturbed. The tail unit was self-supporting and of normal construction. The nose wheel landing gear was fully retractable, the main wheels were retracted laterally into the fuselage.
Technical specifications
| Parameter | La-150 | La-152 |
|---|---|---|
| Conception | Experimental jet fighter | |
| crew | 1 | |
| span | 8.20 m | |
| length | 9.42 m | 9.40 m |
| height | 4.10 m | k. A. |
| Wing area | 12.50 m² | |
| Empty mass | 2,059 kg | |
| Takeoff mass | 3,338 kg | 3,239 kg |
| Engine | one RD-10 (static thrust 8.9 kN) | |
| Top speed | 805 km / h at an altitude of 5,000 m | 778 km / h at an altitude of 5,000 m |
| Ascent time to 5,000 m | 7.2 min (695 m / min) | 6.5 min |
| Summit height | 12,500 m | |
| Range | 500 km (flight time 55 min) | |
| Armament | two 23 mm MK NS-23 (150 rounds each) on the side of the nose wheel shaft |
three 23 mm MK NS-23 (150 rounds each) on the side of the fuselage |
