A novel surrogate model is proposed in lieu of computational-fluid-dynamics solvers, for fast nonlinear aerodynamic and aeroelastic modeling. A nonlinear function is identified on selected interpolation points by a discrete empirical interpolation method. The flowfield is then reconstructed using a least-square approximation of the flow modes extracted by proper orthogonal decomposition. The aeroelastic reduced-order model is completed by introducing a nonlinear mapping function between displacements and the discrete empirical interpolation method points. The proposed model is investigated to predict the aerodynamic forces due to forced motions using a NACA 0012 airfoil undergoing a prescribed pitching oscillation. To investigate aeroelastic problems at transonic conditions, a pitch/plunge airfoil and a cropped delta wing aeroelastic models are built using linear structural models. The presence of shock waves triggers the appearance of limit-cycle oscillations, which the model is able to predict. For all cases tested, the new reduced-order model shows the ability to replicate the nonlinear aerodynamic forces and structural displacements and reconstruct the complete flowfield with sufficient accuracy at a fraction of the cost of full-order computational-fluid-dynamics model.


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    Title :

    Nonlinear Aerodynamic and Aeroelastic Model Reduction Using a Discrete Empirical Interpolation Method


    Contributors:

    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Local classification TIB:    770/7040





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