Accurate computation of drag for a wing/body configuration using multi-block, structered-grid CFD technology

O.J. Boelens, M. Laban, C.M. van Beek, O.J. Boelens

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    Abstract

    In this report the contribution of the National Aerospace Laboratory NLR to the ’CFD Drag Pre- diction Workshop’ organized by the AIAA in Anaheim, CA, on June 9-10, 2001, is presented. This contribution consists of both the results of all test cases and a discussion on the accurate computation of drag coefficients. Two approaches are presented and discussed. The first method performs a grid convergence study using a sequence of nested grids yielding the grid-converged drag coefficient. To enable this study to be carried out, such a sequence of nested multi-block structured grids (’NLR’ grid) has been generated. The second method, using one grid only, de- composes the drag coefficient into its ’physical components’ (vortex, wave and viscous drag). As a consequence, this method provides the aerodynamic designer with a helpful tool, because of its diagnostic potential.
    Original languageUndefined
    Place of PublicationAmsterdam
    PublisherNationaal Lucht- en Ruimtevaartlaboratorium
    Number of pages42
    Publication statusPublished - 2001

    Publication series

    NameNLR-TP-2001-
    PublisherNationaal Lucht- en Ruimtevaartlaboratorium
    No.321

    Keywords

    • IR-76825
    • METIS-201385
    • EWI-16281

    Cite this

    Boelens, O. J., Laban, M., van Beek, C. M., & Boelens, O. J. (2001). Accurate computation of drag for a wing/body configuration using multi-block, structered-grid CFD technology. (NLR-TP-2001-; No. 321). Amsterdam: Nationaal Lucht- en Ruimtevaartlaboratorium.