Abstract
A comparative study is made of three finite volume formulations to investigate the efficacy of flux limiters and damping coefficients on three-dimensional Euler and Navier-Stokes solutions. Spatial discretizations of convective and diffusive fluxes based on a central, a modified central and an upwind schemes are described. The system of ordinary equations is then solved by a factored implicit stepping technique for the computation of supersonic flow over a blunt delta wing. The modified central method, stabilized by flux limiters and a second-order damping, provides high-resolution, non-oscillatory shocks comparable to the characteristic-damped upwind method. It also yields as accurate solutions for viscous flows as the central scheme blended with second- and fourth-order damping.
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Communicated by T.E. Tezduyar, July 10, 1992
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Li, C.P. Implicit finite volume methods and application to a delta wing problem. Computational Mechanics 11, 408–420 (1993). https://doi.org/10.1007/BF00350096
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DOI: https://doi.org/10.1007/BF00350096