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Experimental and Numerical Visualisation of Supersonic Flow over the British Isles

  • Craig White
  • Konstantinos Kontis
Conference paper

Abstract

Colour schlieren experimental results for Mach 5 flow over an arbitrary geometry that generates complex shock structures and shock interactions are presented. The experiment is rebuilt using the rhoCentralFoam solver to solve the compressible Navier–Stokes equations and a numerical analogue, the density gradients (i.e. pseudo-schlieren), is compared to the experimental result, showing very good qualitative agreement. The numerical results give data that can be post-processed to visualise the shock waves by taking advantage of changes in pressure, entropy, velocity, etc. across a shock, in addition to the gradients of density. It is shown that, at least for the geometry and Mach number studied here, the divergence of the velocity field produces the best numerical shock detection method.

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Copyright information

© Springer International Publishing AG, part of Springer Nature 2018

Authors and Affiliations

  1. 1.Aerospace Sciences Division, School of EngineeringUniversity of GlasgowGlasgowUK

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