Abstract:
An efficient three-dimensionasl tructured solver for the Euler and
Navier-Stokese quations is developed based on a finite volume upwind algorithm
using Roe fluxes. Multigrid and optimal smoothing multi-stage time stepping accelerate convergence. The accuracy of the new solver is demonstrated for inviscid
flows in the range 0.675 :5M :5 25. A comparative grid convergence study for
transonic turbulent flow about a wing is conducted with the present solver and
a scalar dissipation central difference industrial design solver. The upwind solver
demonstrates faster grid convergence than the central scheme, producing more
consistent estimates of lift, drag and boundary layer parameters. In transonic
viscous computations, the upwind scheme with convergence acceleration is over
20 times more efficient than without it. The ability of the upwind solver to compute
viscous flows of comparable accuracy to scalar dissipation central schemes
on grids of one-quarter the density make it a more accurate, cost effective alternative.
In addition, an original convergencea cceleration method termed shock
acceleration is proposed. The method is designed to reduce the errors caused by
the shock wave singularity M -+ 1, based on a localized treatment of discontinuities.
Acceleration models are formulated for an inhomogeneous PDE in one
variable. Results for the Roe and Engquist-Osher schemes demonstrate an order
of magnitude improvement in the rate of convergence. One of the acceleration
models is extended to the quasi one-dimensiona Euler equations for duct flow.
Results for this case d monstrate a marked increase in convergence with negligible
loss in accuracy when the acceleration procedure is applied after the shock
has settled in its final cell. Typically, the method saves up to 60% in computational
expense. Significantly, the performance gain is entirely at the expense of
the error modes associated with discrete shock structure. In view of the success
achieved, further development of the method is proposed.
