Abstract
| Original language | English |
|---|---|
| Pages (from-to) | 276-293 |
| Number of pages | 18 |
| Journal | Computers and Fluids |
| Volume | 157 |
| Early online date | 1 Sep 2017 |
| DOIs | |
| Publication status | Published - 3 Nov 2017 |
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Keywords
- supersonic aerodynamics
- shock estimation
- mesh generation
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Shock-conforming mesh generation for aerodynamic analyses at supersonic regimes. / Herrera Montojo, Javier; Fossati, Marco; Minisci, Edmondo.
In: Computers and Fluids, Vol. 157, 03.11.2017, p. 276-293.Research output: Contribution to journal › Article
TY - JOUR
T1 - Shock-conforming mesh generation for aerodynamic analyses at supersonic regimes
AU - Herrera Montojo, Javier
AU - Fossati, Marco
AU - Minisci, Edmondo
PY - 2017/11/3
Y1 - 2017/11/3
N2 - A shock estimation approach is proposed in the context of the generation of shock-conforming meshes for the numerical analysis of inviscid, steady, supersonic and hypersonic flows. For given flow conditions and vehicle’s geometry, the method provides a fast estimation of the shock waves pattern such that grid points can be clustered along the shock waves in a judicious manner. In this way, the uncertainty on mesh generation for shock-dominated flows is reduced and the use of adaptive mesh refinement could be made more efficient or, in some cases, even considered not necessary. The approach is verified against two and three-dimensional supersonic flows for conceptual exemplary geometries like wedges and revolution bodies and more real-world vehicles configurations like rockets and hypersonic aircraft. Qualitative and quantitative assessment of the solution-mesh pair quality is proposed to evaluate the quality of the resulting shock-conforming meshes.
AB - A shock estimation approach is proposed in the context of the generation of shock-conforming meshes for the numerical analysis of inviscid, steady, supersonic and hypersonic flows. For given flow conditions and vehicle’s geometry, the method provides a fast estimation of the shock waves pattern such that grid points can be clustered along the shock waves in a judicious manner. In this way, the uncertainty on mesh generation for shock-dominated flows is reduced and the use of adaptive mesh refinement could be made more efficient or, in some cases, even considered not necessary. The approach is verified against two and three-dimensional supersonic flows for conceptual exemplary geometries like wedges and revolution bodies and more real-world vehicles configurations like rockets and hypersonic aircraft. Qualitative and quantitative assessment of the solution-mesh pair quality is proposed to evaluate the quality of the resulting shock-conforming meshes.
KW - supersonic aerodynamics
KW - shock estimation
KW - mesh generation
UR - http://www.sciencedirect.com/science/article/pii/S0045793017303250
U2 - 10.1016/j.compfluid.2017.08.037
DO - 10.1016/j.compfluid.2017.08.037
M3 - Article
VL - 157
SP - 276
EP - 293
JO - Computers and Fluids
JF - Computers and Fluids
SN - 0045-7930
ER -