A preliminary study of relaxation methods for the inviscid conservative gasdynamics equations using flux splitting
Joseph L. Steger, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1981 - Iterative methods (Mathematics) - 53 pages
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12 percent thick 33 grid 6F F AIAA Paper Appendix area ratio Brandt central difference coarse grid Computational Fluid Dynamics Conference on Numerical Convergence history Convergence rates defined difference equations difference operators dimensional nozzle flow discontinuous first derivative eigenvalues Euler equations factored form finest grid Finite Difference flux vector split full approximation Grid Iterations Fig implicit scheme indicated in figure Inviscid Jacobian matrix linear interpolation Mach number Methods in Fluid minus flux vector Mth grid Multi-Level Adaptive multigrid method multigrid procedure multigrid relaxation multigrid scheme multigrid sweep NASA nine point grid nonlifting biconvex airfoil Numerical Methods Numerical Solution obtained partial differential equations plus-minus flux split Potential Flow Problems rate of convergence relaxation algorithms Relaxation Methods relaxation parameters scheme is given Seventh International Conference shown in figure sonic line split forms Steger surrogate equation approach Transonic Nozzle Flow variable vector split schemes