The aim of the present work is to determine experimental drag coefficients for spherical particles accelerated in shock-tube. Then, validations of two phase flow calculations dealing with solid propulsion rocket in supersonic flight are undertaken. First, experiments in the multi-phase vertical-horizontal shock-tube have been set up at IUSTI in Marseille. The drag coefficient is determinated for particle Reynolds numbers less than 50000 and for particle Mach numbers less than 1.14 and is compared with those found in literature. Second, calculation of two phase flow in solid rocket plume has been performed. The particles are tracked with a stochastic one-way coupling lagrangian method.

Volume Subject Area:
Cavitation and Multiphase Flow
Topics:
Exhaust systems, Plumes (Fluid dynamics), Two-phase flow, Particulate matter, Drag (Fluid dynamics), Rockets, Shock tubes, Flight, Mach number, Propulsion, Reynolds number
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Copyright © 2002
 by ASME
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