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 - 53 pages
What people are saying - Write a review
We haven't found any reviews in the usual places.
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 dimension 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 Jacobian matrices Jacobian matrix linear interpolation Mach number matrix 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 rate of convergence relaxation algorithms Relaxation Methods relaxation parameters scheme is given second order Seventh International Conference shown in figure sonic line sound speed split forms Steger surrogate equation approach Tm+1 u-uQ variable vector split schemes