A preliminary analysis of flow about the blunt trailing edge of the NACA 0012 and supercritical airfoils in transonic speed was made utilizing a 2-D time-averaged Navier-Stokes code with the turbulence model of Baldwin and Lomax. A very fine mesh distribution was focused at the trailing edge region which conventional codes treat as a sharp trailing edge with zero thickness. Computation was made for the NACA 0012 airfoil with three kinds of trailing edge thicknesses, cusp-type sharp, standard and 1 percent thickness and was compared with the result of a conventionally-treated trailing edge. A fifteen percent thickness supercritical airfoil with a trailing edge thickness of 0.5 percent was also analyzed. It was found that a vortex shedding similar to the Karman vortices is formed and surface pressure near the trailing edge shows unsteady oscillation due to the vortices. The magnitude and periodicity of the oscillation is governed by the bluntness. Also, it was shown that the Kutta condition is not necessarily satisfied for the blunt trailing edge.


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    Title :

    Blunt Trailing Edge Analysis of Supercritical Airfoils by a Navier-Stokes Code


    Contributors:
    N. Hirose (author) / N. Kamiya (author)

    Publication date :

    1990


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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