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Robust and Accurate Shock Capturing Method for High-Order Discontinuous Galerkin MethodsA simple yet robust and accurate approach for capturing shock waves using a high-order discontinuous Galerkin (DG) method is presented. The method uses the physical viscous terms of the Navier-Stokes equations as suggested by others; however, the proposed formulation of the numerical viscosity is continuous and compact by construction, and does not require the solution of an auxiliary diffusion equation. This work also presents two analyses that guided the formulation of the numerical viscosity and certain aspects of the DG implementation. A local eigenvalue analysis of the DG discretization applied to a shock containing element is used to evaluate the robustness of several Riemann flux functions, and to evaluate algorithm choices that exist within the underlying DG discretization. A second analysis examines exact solutions to the DG discretization in a shock containing element, and identifies a "model" instability that will inevitably arise when solving the Euler equations using the DG method. This analysis identifies the minimum viscosity required for stability. The shock capturing method is demonstrated for high-speed flow over an inviscid cylinder and for an unsteady disturbance in a hypersonic boundary layer. Numerical tests are presented that evaluate several aspects of the shock detection terms. The sensitivity of the results to model parameters is examined with grid and order refinement studies.
Document ID
20110013250
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Atkins, Harold L.
(NASA Langley Research Center Hampton, VA, United States)
Pampell, Alyssa
(Southern Methodist Univ. Dallas, TX, United States)
Date Acquired
August 25, 2013
Publication Date
June 27, 2011
Subject Category
Numerical Analysis
Report/Patent Number
NF1676L-11718
Report Number: NF1676L-11718
Meeting Information
Meeting: 20th AIAA Computational Fluid Dynamics Conference
Location: Honolulu, HI
Country: United States
Start Date: June 27, 2011
End Date: June 30, 2011
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 599489.02.07.07.04.11.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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