To suppress the stall on an NACA 0012 airfoil, a thin plate (hereafter referred to as a burst control plate) was attached on the airfoil to delay the burst of laminar separation bubbles formed at the stall angle. The burst control plate is used to enhance the vortical structures in the separated shear layer. Wind-tunnel tests were conducted at a chord Reynolds number of 1.3 x 10E5. Flow visualization tests and surface pressure measurements showed that the burst control plate placed on the airfoil suppresses the bubble burst at a wide range of angle of attack and therefore, both the stall angle and the maximum lift coefficient are increased. The particle image velocimetry measurements indicated that when the angle of attack ofthe airfoil with the burst control plate is set higher than the stall angle ofthe original airfoil, a similar flow structure of the original airfoil was observed.


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    Title :

    Airfoil stall suppression by use of a bubble burst control plate


    Additional title:

    Unterdrückung des Strömungsabrisses am Tragflügel durch Anwendung einer Luftleitblech-Steuerplatte


    Contributors:

    Published in:

    AIAA Journal ; 47 , 2 ; 322-330


    Publication date :

    2009


    Size :

    9 Seiten, 15 Bilder, 35 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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