Aerodynamic stall is an important phenomenon in a number of types of fluid machinery. In most cases it is advantageous to operate in an unstalled condition, but as near the stall threshold as possible. Operation in the stall regime produces negative effects such as loss of lift, increased drag, buffeting, and in some cases, control problems. Lifting surfaces subjected to time-dependent changes in freestream velocity or to time-dependent body motions may, in addition, encounter dynamic stall. The occurence of dynamic stall presents additional complications, since the stall threshold may be significantly either above or below that of the static stall threshold. Notable examples of fluid machinery with the potential for dynamic stall problems include axial flow turbines and compressors with inlet distortions, fixed wing aircraft undergoing maneuvers, and helicopters in forward flight. Development of a two-dimensional dynamic stall model along with some preliminary results from the model. This model is based upon fundamental principles which include interactions between the airfoil boundary layers, the separated wake regions shed from the airfoil, and the inviscid flow region. The potential flow region near the airfoil is modeled using a doublet panel analysis, while the separated wake regions are modeled utilizing the concept of discrete vortex sheets. The unsteady boundary layer is modeled using a momentum integral technique. (DePo)


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    Title :

    A preliminary dynamic stall model using a vortex panel method


    Additional title:

    Ein vorbereitendes dynamisches Abrissmodell unter Anwendung der Wirbelpaneelmethode


    Contributors:
    Strickland, J.H. (author) / Oler, J.W. (author) / Im, B.J. (author) / Smith, T.G. (author)

    Published in:

    Publication date :

    1981


    Size :

    7 Seiten, 4 Bilder, 43 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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