TY - JOUR

T1 - Damped, direction-dependent multigrid for hypersonic flow computations

AU - Koren, B.

AU - Hemker, P.W.

PY - 1991

Y1 - 1991

N2 - A nonlinear multigrid technique with improved robustness is developed for the solution of the steady Euler equations. The system of nonlinear equations is discretized by an upwind finite volume method. Collective symmetric point Gauss-Seidel relaxation is applied as the standard smoothing technique. In case of failure of the point relaxation, a switch is made to a local evolution technique. The novel robustness improvements to the nonlinear multigrid method are a local damping of the restricted defect, a global upwind prolongation of the correction and a global upwind restriction of the defect. The defect damping operator is derived from a two-grid convergence analysis. The upwind prolongation operator is made such that it is consistent with the upwind finite volume discretization. It makes efficient use of the P-variant of Osher's approximate Riemann solver. The upwind restriction operator is an approximate adjoint of the upwind prolongation operator. Satisfactory convergence results are shown for the computation of a hypersonic launch and reentry flow around a blunt forebody with canopy. For the test cases considered, it appears that the improved multigrid method performs significantly better than a standard nonlinear multigrid method. For all test cases considered it appears that the most significant improvement comes from the upwind prolongation, rather than from the upwind restriction and the defect damping.

AB - A nonlinear multigrid technique with improved robustness is developed for the solution of the steady Euler equations. The system of nonlinear equations is discretized by an upwind finite volume method. Collective symmetric point Gauss-Seidel relaxation is applied as the standard smoothing technique. In case of failure of the point relaxation, a switch is made to a local evolution technique. The novel robustness improvements to the nonlinear multigrid method are a local damping of the restricted defect, a global upwind prolongation of the correction and a global upwind restriction of the defect. The defect damping operator is derived from a two-grid convergence analysis. The upwind prolongation operator is made such that it is consistent with the upwind finite volume discretization. It makes efficient use of the P-variant of Osher's approximate Riemann solver. The upwind restriction operator is an approximate adjoint of the upwind prolongation operator. Satisfactory convergence results are shown for the computation of a hypersonic launch and reentry flow around a blunt forebody with canopy. For the test cases considered, it appears that the improved multigrid method performs significantly better than a standard nonlinear multigrid method. For all test cases considered it appears that the most significant improvement comes from the upwind prolongation, rather than from the upwind restriction and the defect damping.

U2 - 10.1016/0168-9274(91)90067-A

DO - 10.1016/0168-9274(91)90067-A

M3 - Article

SN - 0168-9274

VL - 7

SP - 309

EP - 328

JO - Applied Numerical Mathematics

JF - Applied Numerical Mathematics

IS - 4

ER -