Calculation of gas flow in shock tube of variable section

Ivanov, M. Ya.

doi:10.1007/bf01019289

Cited by 1 publication

(1 citation statement)

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“…At that time, however, a direct numerical simulation of the §ow in a hypersonic shock tunnel was impossible because of limitations of computers£ capabilities. The ¦rst steps on the computational simulation of the gas §ow in a shock tube with an adjacent convergent-divergent nozzle were made, apparently, in the very late 1960s (see, e. g., [2]). Since then, many separate aspects of the gas §ow in a shock tube and in nozzles have been investigated numerically.…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of dusty gas flow in a hypersonic shock tunnel

Tsirkunov

Verevkin

2013

Progress in Flight Physics

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The results of a computational simulation of an unsteady two-phase gas particle §ow in a hypersonic shock tunnel with a convergent-divergent nozzle are described. In calculations, the con¦guration of the tunnel and the initial gas and particles£ parameters were taken the same as in experiments carried out at the Central AeroHydroDynamic Institute (TsAGI) (Russia). The designed Mach number at the nozzle exit is M = 6.01. Particles are injected into the high-pressure chamber of the shock tube just before the diaphragm opening. The carrier gas §ow is described by the Euler equations which are solved by a ¦nite-volume method of the second order. The particle-phase motion is simulated using the Lagrangian method. Developing in time a two-phase §ow is investigated from the instant of opening the diaphragm between the high-and low-pressure chambers of the shock tube to the end of the quasi-steady-state §ow over a model in the test section. Flow properties of both phases are discussed with emphasis on the problems that can appear in experiments.

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Section: Introductionmentioning

confidence: 99%