Alexeyev I-211
| Alexeyev I-211 / I-215 | |
|---|---|
| Type: | Interceptor aircraft |
| Design country: | |
| Manufacturer: | |
| First flight: |
1947 |
| Production time: |
1946-1947 |
| Number of pieces: |
2 |
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The Alexejew I-211 ( Russian Алексеев И-211 ) is a single-seat, Soviet long-range interceptor aircraft with two TL engines.
development
In June 1946, immediately after the OKB Lavochkin was relocated and divided into three plants in 1945, the previous deputy of the general designer Semyon Michailowitsch Alexejew , who already had a large share in the La-5 and La-7 and in the construction of the La -15 had already gained experience in the construction of jet aircraft, carried out his own development work in his new OKB-21.
The first machine was the I-211 in early 1947. The flight test was carried out by A. A. Popow and A. A. Jefremow in the autumn of the same year, which was completed without any problems.
Because of the poor performance and reliability of the TR-1 engines, a second machine under construction was converted to RD-500 engines (an unlicensed replica of the Rolls-Royce Derwent engine) before completion and flew as Alexejew I-215 at the end of 1947. A series production was not decided, however, both machines remained test samples. Even an I-211 equipped with swept wings remained just a project.
Construction and armament
The I-211 had an all-metal cell in shell construction with a pressurized cabin and a circular fuselage cross-section. At the stern there were two square air brake flaps that were supposed to prevent the aircraft from breaking the sound barrier during a dive. They activated themselves automatically at critical flight speeds, but could also be operated manually by the pilot. There was a powerful searchlight in the bow tip, which was intended for optical target search and for landing aid at night. A radar device could be installed in exchange. There were also three fuel tanks with a total volume of 2000 liters in the fuselage.
The wing had a trapezoidal outline and a laminar profile designed by ZAGI . There were slats on the leading edge which extended by 20 ° on take-off and 45 ° on landing. Two disposable additional fuel tanks with 250 liters each could be carried externally.
The newly developed Ljulka AL-1 (TR-1) was used as the engine. Due to the generous size, RD-45 engines could also be used. The installation of series cameras was planned for a reconnaissance variant .
Two variants were planned as armament, which were interchangeable within a short time. The first version comprised three N-37 cannons with 30 rounds each, or four to six 23 mm cannons, installed between the pressurized cabin and nose wheel shaft. The second consisted of two cannons each of 57 and 75 mm caliber. Overall, a weapon or camera load of up to a ton could be carried.
Technical specifications
| Parameter | Data |
|---|---|
| Conception | Interceptor and reconnaissance aircraft |
| constructor | Semyon Alexeyev |
| Years of construction | 1946/47 |
| crew | 1 |
| length | 11.45 m |
| height | 4.32 m |
| Wingspan | 12.25 m |
| Wing area | 25.00 m² |
| Empty mass | 4,360 kg |
| Takeoff mass | normal 6,650 kg maximum 7,450 kg |
| Engines | two Lyulka TR-1A |
| power | 14.7 kN each |
| Top speed | 880 km / h at an altitude of 8,000 m, 950 km / h at a height of 4,000 m, 935 km / h near the ground |
| Flight duration | a maximum of 2 h with additional disposable containers up to 3 h |
| Climb performance | 3 min at 5,000 m |
| Service ceiling | 13,600 m |
| Range | normal 1,550 km maximum 1,800 km |
| Armament | three 37-mm- MK arranged around the nose wheel shaft four to six 23-mm-MK or two 57-mm-MK or 75-mm-MK various missiles and weapon loads up to 1,000 kg |
See also
literature
- Helmut F. Walther: The planes of Semjon Alexejew . In: Fliegerrevue . No. 1/1993 .
Individual evidence
- ↑ AIR International, Vol. 12 No. 1, January 1977, PlaneFacts