2011 2(7)

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   Short abstract

 

Pages:

151 - 154

Language:

RU

Ref.:

6


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2011_2(7)_26.pdf

 

 

PROBLEM OF ASYMMETRICAL FLOW SEPARATION FORMATION IN SUPERSONIC NOZZLE

Golub V.V.1, Saveliev A.S.2

1 Joint Institute for High Temperatures RAS, Moscow, Russia
2 Moscow Institute of Physics and Technology (State University), Moscow, Russia


Citation:

Golub, V.V. and Saveliev, A.S., (2011) Problem of asymmetrical flow separation formation in supersonic nozzle, Modern Science: Researches, Ideas, Results, Technologies, Iss. #2(7), PP. 151 - 154.


Keywords:

submerged jet; schlieren visualization; nozzle


Abstracts:

At presented work the high speed schlieren visualization and mesuaremetns of velocity distribution obtained by particle image velocimetry of submerged jet with Mach number M=2 were carried out with supersonic nozzle that operates at overexpanded regime. The parallel algorythm of processing of obtained digital images was developed, and it allows investigating the process of asymmetric separated flow behind the nozzle. With the digital videoregistration of schlieren pictures, digital registration of pressure and with digital processing of obtained images the dependence between the relative (to thrust) value of side loads and pressure ratio was obtained.


References:

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  2. Frey M., Hagemann G. Status of flow separation prediction in rocket nozzles. AIAA Paper 98-3619, 1998.

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  4. Hagemann G., Frey M., Koschel W. Appearance of restricted scock separation in rocket nozzles // J. Propulsion and power, 18, 3, 2002, 577-584.

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