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Hypersonic flow computations around re-entry vehiclesThe development of an algorithm for the solution of the compressible Euler equations at high Mach numbers on unstructured tetrahedral meshes is described. The basic algorithm is constructed in the form of a central difference scheme plus an explicit added artificial viscosity based upon fourth order differences of the solution. The stability of the solution in the vicinity of strong gradients is preserved by the incorporation of an additional artificial viscosity based upon a second order difference. Higher order accuracy is regained by using the ideas of flux corrected transport to limit the amount of added viscosity. The solution is advanced to steady state by means of an explicit multi-stage time-stepping method. The computational efficiency of the complete process is improved by incorporating an unstructured multigrid acceleration procedure. A number of flows of practical interest are analyzed to demonstrate the numerical performance of the proposed approach.
Document ID
Document Type
Conference Paper
Peraire, J.
(Imperial Coll. of Science and Technology London, United Kingdom)
Peiro, J.
(Imperial Coll. of Science and Technology London, United Kingdom)
Morgan, K.
(Wales Univ. Swansea., United States)
Vahdati, M.
(Imperial Coll. of Science and Technology London, United Kingdom)
Molina, R. C.
(European Space Agency. European Space Research and Technology Center ESTEC, Noordwijk, Netherlands)
Date Acquired
August 16, 2013
Publication Date
April 1, 1993
Publication Information
Publication: AGARD, Theoretical and Experimental Methods in Hypersonic Flows
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