Results of an analytical and experimental study of boundary layer flow over an aerodynamic surface rejecting heat to a cool environment. This occurs following reentry of a Space Shuttle vehicle. Analytical studies revealed that a surface to freestream temperature ratio, greater than unity tended to destabilize the boundary layer, hastening transition and separation. Therefore, heat transfer accentuated the effect of an adverse pressure gradient. Wind tunnel tests of a 0012-64 NACA airfoil showed that the stall angle was significantly reduced while drag tended to increase for freestream temperature ratios up to 2.2.


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    Title :

    Surface temperature effect on subsonic stall.


    Contributors:
    Macha, J. M. (author) / Norton, D. J. (author) / Young, J. C. (author)

    Conference:

    American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference


    Publication date :

    1972-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Surface Temperature Effect on Subsonic Stall

    DAVID J. NORTON / JOHN M. MACHA AND JAMES C. YOUNG | AIAA | 1973


    Surface temperature effect on subsonic stall

    MACHA, J. / NORTON, D. / YOUNG, J. | AIAA | 1972




    Numerical Simulation of Rotating Stall in a Subsonic Compressor

    Gourdain, Nicolas / Burguburu, Stéphane / Leboeuf, Francis et al. | AIAA | 2004