TY - CONF
T1 - Multigrid unsteady navier-stokes calculations with aeroelastic applications
AU - Alonso, Juan J.
AU - Martinelli, Luigi
AU - Jameson, Antony
N1 - Funding Information:
This work has benefited froin the generous support of AIII’A under Grant No. N00014-92-.1-179G and AFOSR under Graut No. AFOSR-91-0391. Computational time on the NAS SP2 system was provided RS a part of the IDM-CRA initiative.
Funding Information:
This work has benefited froin the generous support of ARPA under Grant No. N00014-92-J-1796 and AFOSR under Graut No. AFOSR-91-0391. Computational time on the NAS SP2 system was provided RS a part of the IDM-CRA initiative.
Publisher Copyright:
© 1995, by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 1995
Y1 - 1995
N2 - An implicit approach to the solution of the unsteady two-dimensional Navier-Stokes equations is presented. After spatial discretization, the resulting set of coupled implicit non-linear equations is solved iteratively. This is accomplished using well proven convergence acceleration techniquies for explicit schemes such as multigrid, residual averaging, and local time-stepping in order to achieve large computational efficiency in the calculation. Calculations are performed in parallel using a domain decomposition technique with optimized communication requirements. In addition, particular care is taken to minimize the effect of numerical dissipation with flux-limited dissipation schemes. Results for the unsteady shedding flow behind a circular cylinder and for a pitching NACA 64A010 airfoil are presented with experimental comparisons, showing the feasibility of accurate, efficient, time-dependent viscons calculations. Finally, a two-dimensional structural model of the cylinder is coupled with the unsteady flow solution, and time responses of the deflections of the structure are analyzed.
AB - An implicit approach to the solution of the unsteady two-dimensional Navier-Stokes equations is presented. After spatial discretization, the resulting set of coupled implicit non-linear equations is solved iteratively. This is accomplished using well proven convergence acceleration techniquies for explicit schemes such as multigrid, residual averaging, and local time-stepping in order to achieve large computational efficiency in the calculation. Calculations are performed in parallel using a domain decomposition technique with optimized communication requirements. In addition, particular care is taken to minimize the effect of numerical dissipation with flux-limited dissipation schemes. Results for the unsteady shedding flow behind a circular cylinder and for a pitching NACA 64A010 airfoil are presented with experimental comparisons, showing the feasibility of accurate, efficient, time-dependent viscons calculations. Finally, a two-dimensional structural model of the cylinder is coupled with the unsteady flow solution, and time responses of the deflections of the structure are analyzed.
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M3 - Paper
AN - SCOPUS:75749116130
T2 - 33rd Aerospace Sciences Meeting and Exhibit, 1995
Y2 - 9 January 1995 through 12 January 1995
ER -