Numerical simulation of supersonic flow over Zenit-2SLБ launch vehicle
Journal Title: Технічна механіка, Техническая механика, Technical Mechanics - Year 2016, Vol 4, Issue 4
Abstract
The results of a numerical simulation of a supersonic flow over the Zenit-2SLБ launch vehicle at angle of attack 5, 15 and 25 degrees are presented. Attention in this work is devoted to obtaining the proved three-dimensional vortex structure of the flow around the Zenit-2SLБ launch vehicle. The numerical simulation is based on the unsteady three-dimensional Reynolds-averaged Navier–Stokes equations for a compressible gas. Refer-ence equations are solved by the control volume method. From computations three characteristic regimes of the flow around a rocket body at angle of attack are obtained, including a nonstalling flow around a cylindrical body part, attached and unattached separation of flow at cross section. The simulation results correlate satisfactorily with the existing computations and experimental data.
Authors and Affiliations
N. Grishin, A. Prikhodko
Keywords
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