The development of the MiG-8 carried out to check the controllability and stability of aerodynamic configuration "duck". The project is supervised OKB-155. In addition to checking the new scheme, as practiced job-swept wing and tricycle landing gear with the presence of the front support.
Work on the project began in February 45 years. First started the elaboration of the layout. The main credit for the majority of the work should be given to advanced engineers N. Matyuk, Andrianov, K. Pelenbergu A. Chumachenko and J. Szelecki. According to preliminary calculations, the maximum speed "Ducks" should not exceed the value in 240 km / h. Actually, the theory is confirmed through wind tunnel T-102, located in TsAGI.
But she could not completely purge show structural stability in critical conditions. Specialists of TsAGI advised to make its first flight to the established fixed end slats. Their magnitude scale corresponds to the ailerons. But before the first flight of the leading engineer Matveev categorically not recommended to start the test with near-critical conditions. In his argument it appeared that in relation to the properties of snap a "duck" is very unfavorable.
TsAGI was performed a lot of calculations and conducted several tests to determine the near-critical flutter speed and natural frequency. According to the data revealed that the aircraft is capable of speeds in 328 km / h, and the maximum is 270 km / h. Static tests of the MiG-8 brought to the operational load, which amounted to 67% of the failure.
The first MiG-8 took to the skies on August 13 45 years. He led the test pilot Alexander Zhukov. To help Zhukov management "Duck" appointed representatives of LII A. Grinchik. Flight tests have been divided into several stages. First decided to carry out in the period from late August to mid-September of that year. It took place on the territory of LII NCAP. It was decided to play it safe, and to improve safety on the aircraft installed end slats with a constant gap.
The result of the test for resistance has been quite successful, as it was found out that the plane has a positive alignment with the longitudinal strength, the same track and cross. It is recommended to TsAGI for this result, lead to the reverse V-wing cross by one degree, and the final goals to expand 10 degrees inward ends of the wing. On the toe of the elevator specifically put cargo in 1 kg to align sustainability features with the free and fixed wheel.
In addition, experts from LII issued some recommendations for refinement of the aircraft. For this "duck" at the end of the year 1945 sent to the factory №155. There's engineers began working on improving, in particular moved the keels on the middle console, set driven trimmer on the elevator and rudder beefed compensator. In addition, on the front rack have built the wheel size 500h150.
To test the new aircraft brought to the factory airfield in February 1946 years. After several flights, the designers found one negative nuance. Engine oil temperature does not rise above the mark 20 ° C. After the study it was found out that the reason is the absence of (deleted) fairings. They put back. The next flight took place on February 28, but instead raise the temperature observed in its excess. MiG-8 was sent back for revision.
Third, the MiG March 1946-8 ferried back to LII NCAP. Thus began the second phase of flight tests. It includes tests related to aircraft snap properties. During the test, the wing began a new revision. Installed ending with considerable negative angle cross V and removed the slats. But there were fears of a snap properties MiG-8 did not materialize.
Studies have shown that as soon as the driver enters into a tailspin, you should immediately release the steering wheel, and the device itself will be released out of it instantly. Fixed a pusher propeller has created the ability to check the handling of the aircraft at low speeds without blowing the wing screw. Also, they figured out a way of air handling unit on the ground and the nuances of the landing and takeoff in the absence of a screw blower controls. In the future, these results were used in the creation of MiG jet fighters and MiG-9-15. After all the testing and approval "Duck" in 1946 year began to be used as a transport plane and connected OKB. It is unique in that it has never been in an emergency situation.
The design of the MiG-8 «Duck»
MiG-8 made under the scheme strut-braced high with non-retractable tricycle landing gear. The frame of the fuselage is constructed of pine sticks and has a plywood sheathing. Enclosed cab is designed for one pilot and two passengers. A door located on the left side of the fuselage. Excellent visibility and forehand sides ensured through good cockpit glazing. Horizontal tail installed on the beam, located at the end of the forward fuselage. At the same time the tail portion goes into the engine compartment, which ends cook screw.
Wing dvuhlonzheronnoe type with a relatively uniform thickness along the span (12%) has a set of wooden and canvas siding. Designed on the profile of the wing, "Clark UN." The installation angle corresponds to two degrees. Vertical tail wing mounted at the ends represented washers. The ailerons are created on a "Fries". They are made of duralumin frame and fabric covering.
The area of the vertical stabilizer of 3 m2, Horizontal - 2,7 m2. Its scope - 3,5 m. Keely wooden rails rudders are composed of duralumin frame and fabric covering. The composition of the elevator is the same. Wooden stabilizer. Management ailerons and rudders Rope, elevator - tough.
The power plant is represented by motor M-11 FM air cooling. Its power reaches 110 hp Two-bladed wooden propeller pushing a constant pitch. Its diameter - 2,35 m. The propeller blades are installed at an angle of 24 degree. Motorama welded tubular. The engine is fully zakopotirovan and has separate blowouts for each cylinder. Pneumatic run. The fuel stored in tanks in two Dural that set in the main part of each wing. The total capacity of the tanks - 118 l. Behind the passenger cabin located oil tank capacity l 18.
Landing gear of the welded metal. Depreciation of the air-oil. Nose wheel has a diameter 300h150, and the rack is equipped with a damper.
MiG-8 Environmental Specifications:
|Aircraft Length m||6.80|
|Wing area, m2||15.00|
|engine's type||1 PD M-11FM|
|Power, HP||X 1 110|
|Maximum speed km / h||215|
|Practical range, km||500|
|Practical ceiling, m||5200|
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