A comparison of finite volume flux vector splittings for the Euler equationsA comparison is made between the computational results of the Steger-Warming (1981) and van Leer (1982) flux splitting methods, which have been applied in generalized coordinates to quasi-one-dimensional transonic flow in a nozzle and two-dimensional subsonic, transonic, and supersonic flow over airfoils. The latter splitting method leads to higher convergence rates and a sharper representation of shocks in the transition region. The second-order accurate, one-sided-difference model is extended to a third-order, upwind-biased model with only small additional computational effort.
Document ID
19850037382
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Anderson, W. K. (NASA Langley Research Center Hampton, VA, United States)
Thomas, J. L. (NASA Langley Research Center Hampton, VA, United States)
Van Leer, B. (Delft Technische Hogeschool, Delft, Netherlands)