Experimental results and analysis of the effects of boundary layer tripping on dynamic stall of a transiently pitching airfoil are presented. At low Mach numbers, the tripped airfoil exhibits qualitative similarity with the behavior of the untripped airfoil. However, the local supersonic flow at Mach numbers greater than 0.3 is significantly modified by the trip leading to vastly different shock/boundary layer interactions, dynamic stall onset and vortex formation angles. The formation of the laminar separation bubble is found to have a favorable influence in delaying dynamic stall on the untripped airfoil flow. In both Mach number regimes, the tripped flow actually stalls at slightly lower angles of attack. Further experimentation with three trips on an oscillating airfoil showed that the dynamic stall process is very sensitive to the state of the turbulence in the boundary layer. This sensitivity points to a need for finer turbulence modeling techniques for use in dynamic stall computations.


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    Title :

    Transition effects on compressible dynamic stall of transiently pitching airfoils


    Contributors:

    Conference:

    AIAA, Fluid Dynamics Conference ; 1993 ; Orlando, FL, United States


    Publication date :

    1993-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Transition Effects on Compressible Dynamic Stall of Transiently Pitching Airfoils

    M. C. Wilder / M. S. Chandrasekhara / L. W. Carr | NTIS | 1993



    Transition Effects on Compressible Dynamic Stall of Transiently Pitching Airfoils

    Wilder, M. C. / Chandrasekhara, M. S. / Carr, L. W. et al. | British Library Conference Proceedings | 1993