Pitch/plunge equivalence for deep dynamic stall of a straight finite wing is considered by employing large-eddy simulations. The flowfields are computed with a well-established time-implicit high-fidelity large-eddy simulation approach. The wing has a moderate aspect ratio of AR = 4 and a NACA 0012 section incorporating a rounded tip. The flow parameters are a freestream Mach number of M = 0.1 and chord Reynolds numbers of R e c = 2 × 10 5 . Pure pitching and equivalent plunging maneuvers are considered with a reduced frequency of k = π f c / U = π / 16 and minimum and maximum effective angles of attack of 4 and 22 deg, respectively. The pitch and plunge dynamic stall cases are compared in detail in terms of the unsteady three-dimensional flow structure, surface pressure, and loading. Differences in the lift and moment coefficient are shown to be correctable, employing a steady thin-airfoil theory for a cambered airfoil that accounts for the rotation-induced apparent camber present in the pitching case. This pitch/plunge equivalence is extendable to the dynamic stall of a swept wing, as demonstrated in another paper by the authors [“Pitch–Plunge Equivalence for Dynamic Stall of Swept Finite Wings,” AIAA Journal (submitted for publication)].


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    Title :

    Pitch/Plunge Equivalence for Dynamic Stall of Unswept Finite Wings


    Contributors:

    Published in:

    AIAA Journal ; 60 , 8 ; 4807-4817


    Publication date :

    2022-04-29


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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    Garmann, Daniel J. / Visbal, Miguel R. | AIAA | 2022




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