Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||393 - 414|
|Section||Chapter Six. Hypersonics|
|Published online||14 June 2013|
Numerical analysis of dusty gas flow in a hypersonic shock tunnel
Baltic State Technical University, Faculty of Aerospace Engineering 1 First Krasnoarmeiskaya Str., St. Petersburg 190005, Russia
The results of a computational simulation of an unsteady two-phase gas-particle flow in a hypersonic shock tunnel with a convergent-divergent nozzle are described. In calculations, the configuration 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 flow is described by the Euler equations which are solved by a finite-volume method of the second order. The particle-phase motion is simulated using the Lagrangian method. Developing in time a two-phase flow 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 flow over a model in the test section. Flow properties of both phases are discussed with emphasis on the problems that can appear in experiments.
© Owned by the authors, published by EDP Sciences, 2013
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.