| Autor: |
Peter Hartwich, Shreekant Agrawal |
| Rok vydání: |
1997 |
| Předmět: |
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| Zdroj: |
13th Computational Fluid Dynamics Conference. |
| DOI: |
10.2514/6.1997-2038 |
| Popis: |
A highly automated method is presented for rapidly adjusting multiblock patched grids over complex configurations during aerodynamic shape optimization or aeroelastic analyses. A very low level of user-intervention is achieved by making the block boundaries transparent. This is accomplished by employing data structures as they are commonly found in unstructured computational fluid dynamics (CFD) methods, and by basing the relation between a "master" (or solid surface) node and its "slave" nodes solely on minimum distance. The "slave" nodes form the vertices of subgrids (typical size: 5x5 grid points) on grid block faces. These subgrids ensure maintenance of point-matched block interfaces. The "slave" nodes follow the movement of their "master" nodes, scaled by a Gaussian distribution function to preserve the integrity of grids in the presence of multiple body surfaces. Transfinite interpolation is used to transfer the displacement of the slave nodes throughout the entire computational domain. An automated surface regridding capability enhances the robustness of the methodology and improves the grid quality. Effectiveness and efficiency of the grid perturbation method are demonstrated for several applications to High-Speed Civil Transport (HSCT) wing/body (W/B) and wing/body/nacelle/diverter (W/B/N/D) configurations. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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