February 4, 1959 issued a decree on the construction of 111-48 sport single Yak-104PS (future Yak-32 ) with the engine RU19-300. October 13, 1960, ahead of the deadlines set at 4.5 months, OKB built the first single sport aircraft Yak-32 ( "32"). It is intended for testing technology of flight operations in a circle route, training in adverse weather conditions, day and night, as well as for testing equipment performance figures and complex aerobatics. Leader of work was K.V.Sinelschikov, lead engineer V.P.Vlasov.
The machine features a lack of rear cockpit, increased to 45 kg supply of fuel in the supply tank for a longer reverse maneuvers, engine adapted to perform inverted flight. By order GKAT of 4 January 1961 in June of that year it was built two Yak-32 (board "60" and "70"). From 17 January to 27 July 1961, two Yak-32 tests were OKB and the LII in training ( "32") and flight-sport ( "60") versions. Aerobatic variant was 555 kg facilitated by reducing the fuel stock and aircraft empty weight (130 kg, including removable equipment weight 25 kg, of which 7.9 kg -this by replacing Collins station to WCP). On a flight option was increased aileron area and no flaps.
Joint testing performed leading test pilot V.P.Smirnov, test pilots V. Mukhin, Yu.V.Petrov, A.P.Bogorodsky pilots flying by - S.N.Anohin, V.M.Volkov, A .L.Kolosov, G.M.Kurkay, I.S.Grigorev. In total 49 flights were carried out with a common touch 23 hours and 22 minutes. In addition, in preparation for the festival in Tushino, and during it, from June 8 to July 9, 1961 was carried out another 55 flights (23 hours 14 minutes flying time). The plane was easy and pleasant to pilot, steady speed and overload, easy to learn, with a spacious cabin and excellent visibility on taxiing and in the air. It performed all the figures forward and reverse maneuvers and complex multi-complexes. . We obtain the maximum speed of 663 km / h at an altitude of 3000 m at a reduction of the aircraft achieved: M = 0.721 and airspeed 765 km / h at an altitude of 2200 m The general conclusion was that the plane "can be recommended as a model of aerobatic aircraft for. flying clubs DOSAAF ". State tests planned for the second quarter of 1961 were not carried out.
In 1961, the Yakovlev aircraft was demonstrated at the Central Airport Defense Minister R.Ya.Malinovskomu the possibility of using the Yak-32 ( "32") as a light attack aircraft from the experience of the Vietnam War. Such a project with the designation Yak-32SH was already prepared in the bureau. Plane with two underwing holders weapons was displayed on the ground in front of him laid out a variety of weapons. According to calculations carried out 25 May 1961, the engine thrust was increased to 1100 kg, fuel tank to make 726 kg. Takeoff weight attack aircraft increased to 2580 kg or 2900 kg for the mass of arms, respectively, 300 and 716 kg. The maximum speed to 685 km / h at an altitude of 5000 m Options suspension:. Gun AO-9 (2x150 kg), missiles of different types (from 2x116 kg to 2x234 kg), AB-250 bombs (2x275 kg) or incendiary tanks ST-360 (2x358 kg).
On the orders of MAP from August 5, 1971, one of the Yak-32 was rebuilt in aerobatic version with experienced RU19P TRD-300, Rod 900 kg. In the engine oil system is changed to provide greater duration inverted flight. The plane was designated Yak-32P. From the original Yak-32, he was distinguished with pressurized cabin ventilation by dynamic pressure, the presence of a connected radio "Lily-5" radio compass ARK-15 and the gyromagnetic compass MMC-1A. Marker receiver, ARC-15 and MMC-1A total weight of 40 kg were made as a removable equipment for use only in the ferry flight, flight route, and in adverse weather conditions.
In 1972, the Yak-32P passed factory tests and control air show in Tushino program demonstrated aerobatics. Flying aircraft evaluation was as good as for the Yak-32. Tests conducted pilots Yu.I.Mitikov, O.A.Bulygin, lead engineer on the aircraft I.A.Mozharov.
|Aircraft Length m||10.14|
|Wing area, m2||14.30|
|Weight, kg empty aircraft||1434|
|engine's type||1 THD RU-19-300|
|Thrust, kgf||1 x 900|
|Maximum speed km / h||663|
|Cruising speed, km / h||540|
|Practical range, km||350|
|Practical ceiling, m||13000|
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