A full Navier-Stokes solver has been used to model transonic flow over three airfoil sections. The method uses a two-dimensional, implicit, conservative finite difference scheme for solving the compressible Navier-Stokes equations. Results are presented as prescribed for the Viscous Transonic Airfoil Workshop to be held at the AIAA 25th Aerospace Sciences Meeting. The NACA 0012, RAE 2822 and Jones airfoils have been investigated for both attached and separated transonic flows. Predictions for pressure distributions, loads, skin friction coefficients, boundary layer displacement thickness and velocity profiles are included and compared with experimental data when possible. Overall, the results are in good agreement with experimental data.


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    Title :

    Analysis of Viscous Transonic Flow over Airfoil Sections


    Contributors:
    D. L. Huff (author) / J. C. Wu (author) / L. N. Sankar (author)

    Publication date :

    1987


    Size :

    32 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Analysis of viscous transonic flow over airfoil sections

    Huff, Dennis L. / Wu, Jiunn-Chi / Sankar, L. N. | NTRS | 1987


    Analysis of viscous transonic flow over airfoil sections

    HUFF, DENNIS / WU, JIUNN-CHI / SANKAR, L. | AIAA | 1987


    Analysis of viscous transonic flow over airfoil sections

    Huff, Dennis L. / Wu, Jiunn-Chi / Sankar, L. N. | NTRS | 1987


    Calculation of Transonic Flow over Supercritical Airfoil Sections

    William C. Rose / Arnan Segine | AIAA | 1978