Yakovlev Yak-1000
The Yakovlev Yak -1000 (Russian Яковлев Як -1000) was one of the numerous test pattern from the Soviet aircraft design bureau Yakovlev, who were tested after the Second World War, in addition to the types of Lavochkin, Mikoyan -Gurevich and Sukhoi to the newly developed jet engines to develop the optimal associated airframes.
History
1945 Soviet engineers began the ZAGI after evaluation of German documents to deal with the problem of a wing for supersonic range. Two directions have been pursued: one is the refinement of the swept wing, the flight behavior was already fairly well known, and secondly, the construction of a triangular wing smallest span, referred to at TsAGI as rhombic wings. In the late 1940s, the development of such a wing was completed and Alexander Yakovlev offered to it to design an airplane.
Designed and built designated as Jak -1000 machine was the end of 1950 to October 1951. Fitted was the guy with one in comparison to the body length very small and extremely thin delta wing with well shaped delta tail, which in an experimental aircraft for the achievement of high speed supersonic suggests. The Jak -1000 should also reach for the then incredible speed of Mach 1.7. At the same time resulted in a 1:1 model for wind tunnel tests in TsAGI. These then were but a calculated top speed of only 1100 km / h
The rolling test on the ground by D. W. Sjusin began on March 3, 1951. Problems with the tandem suspension, which was useless for an aircraft of this type, and expected aerodynamic complications during the flight did a test in the air as too risky appear, therefore the project in June 1951 were abandoned. Nevertheless, the Jak -1000 program was not a complete failure. The delta wing has evolved and took on the built en masse MiG -21 use later.
Technical Description
The Jak -1000 was a cantilever mid -wing monoplane of all-metal monocoque construction and had a suspension in tandem design, that is, two located in the fuselage main wheels carried the weight of the aircraft, two placed in the middle of the wing support wheels ensured the stability on the ground. The dreiholmige and bumpered tenth rib wing had a leading edge sweep of 60 °. The relative profile thickness was 3.4 % at the root and 4.5% in the central part and at the wing tip. The tail unit was designed almost identical. The cockpit was hermetisiert and equipped with an ejection seat.