Abstract
Aeroservoelastic simulation of realistic configurations requires the representation of moving control surfaces. Once a control surface is deflected, for example, at the trailing edge of a wing, the surface is no longer continuous and this is considered here. A sliding grid approach is used to allow control surface deflection within a multiblock-structured grid framework. Two methods of information transfer between patched (non-matching) grids are developed and tested in this paper: the first involving halo interpolation and the second, conservative flux interpolation. Results are presented for a range of test cases involving steady and unsteady flows using non-matching and sliding interfaces at block boundaries. It is shown that both methods can be applied to the example of a wing with a deflected control surface, where no advantage is gained by using a significantly more complex, conservative method.
| Translated title of the contribution | Development and validation of sliding and non-matching grid technology for control surface representation |
|---|---|
| Original language | English |
| Pages (from-to) | 299 - 315 |
| Number of pages | 17 |
| Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
| Volume | 220 |
| Issue number | 4 |
| DOIs | |
| Publication status | Published - Feb 2006 |