The effect of discrete contour bumps on reducing the transonic drag at off-design conditions on an airfoil have been examined. The research focused on fully-turbulent flow conditions, at a realistic flight chord Reynolds number of 30 million. State-of-the-art computational fluid dynamics methods were used to design a new baseline airfoil, and a family of fixed contour bumps. The new configurations were experimentally evaluated in the 0.3-m Transonic Cryogenic Tunnel at the NASA Langley Research center, which utilizes an adaptive wall test section to minimize wall interference. The computational study showed that transonic drag reduction, on the order of 12% - 15%, was possible using a surface contour bump to spread a normal shock wave. The computational study also indicated that the divergence drag Mach number was increased for the contour bump applications. Preliminary analysis of the experimental data showed a similar contour bump effect, but this data needed to be further analyzed for residual wall interference corrections.


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    Title :

    On the Application of Contour Bumps for Transonic Drag Reduction(Invited)


    Contributors:

    Conference:

    43rd AIAA Aerospace Sciences Meeting and Exhibit ; 2005 ; Reno, NV, United States


    Publication date :

    2005-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    On the Application of Contour Bumps for Transonic Drag Reduction (Invited)

    Milholen, W. E. / Owens, L. R. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2005




    Three-dimensional contour bumps for transonic wing drag reduction

    Qin, N / Wong, W S / Le Moigne, A | SAGE Publications | 2008


    Three-dimensional contour bumps for transonic wing drag reduction

    Qin, N. / Wong, W.S. / Le Moigne, A. | Tema Archive | 2008