2014 1(14)

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10 - 16

Language:

RU

Ref.:

17


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DEVELOPMENT OF METHODS TO CALCULATE AEROTHERMODYNAMICS FOR AEROSPACE SYSTEMS IN TRANSITION MODE

Khlopkov Yu.I.1,2, Zharov V.A.1,2, Mio Miint Z.1, Khlopkov A.Yu.1, Polyakov M.S.1

1 Moscow Institute of Physics and Technology (State University), Moscow, Russia
2 Central Aerohydrodynamic Institute, Zhukovskiy, Russia


Citation:

Khlopkov, Yu.I., Zharov, V.A., Mio Miint, Z., Khlopkov, A.Yu. and Polyakov, M.S., (2014) Development of methods to calculate aerothermodynamics for aerospace systems in transition mode, Modern Science: Researches, Ideas, Results, Technologies, Iss. #1(14), PP. 10 - 16.


Keywords:

aerospace system; hypersonic aerothermodynamics; aerodynamics in transition regime; heat transfer; engineering methods


Abstracts:

In this paper considered the development of the methods for aerothermodynamic characteristics research in aerospace systems. In particular, the analysis of mathematical modeling of aerothermodynamic characteristics for aerospace vehicle “Clipper” and hypersonic technology vehicle “Falcon HTV-2” by using local methods are described. The results of calculation of aerothermodynamic characteristics for aerospace system at all range of flight at different Reynolds numbers (from orbital flight to landing mode) are presented. In this paper also described the method (local-bridging method) to calculate the heat transfer coefficient in the transient regime. Presented methods and results can be useful for creating new generation of aerospace system.


References:

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