This work considers aeroelastic modeling of the NACA 0012 benchmark wing, a configuration previously tested in the Transonic Dynamics Tunnel for flutter. Numerical modeling is conducted within the FUN3D Reynolds-averaged Navier–Stokes–based flow solver, with a particular focus on multiscale mesh adaptation and linearized frequency domain computations. Flutter results are obtained and compared with experimental data across a range of flow complexities, including subsonic flows, transonic flows with mild nonlinearities, and separated transonic flows. A reasonable correlation with test data is obtained for the first two categories, but only mixed results are shown for the third category. In all cases, insight into the transonic flutter behavior is obtained via the generalized aerodynamic forces computed through flow linearizations.


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    Titel :

    Transonic Aeroelastic Modeling of the NACA 0012 Benchmark Wing


    Beteiligte:

    Erschienen in:

    AIAA Journal ; 59 , 10 ; 4134-4143


    Erscheinungsdatum :

    01.10.2021




    Medientyp :

    Aufsatz (Konferenz) , Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    TRANSONIC AEROELASTIC MODELING OF THE NACA 0012 BENCHMARK WING

    Stanford, Bret / Jacobson, Kevin E. / Massey, Steven | TIBKAT | 2020


    Transonic Aeroelastic Modeling of the NACA 0012 Benchmark Wing

    Bret Stanford / Kevin Jacobson / Steven Massey | NTRS


    Transonic Aeroelastic Modeling of the NACA 0012 Benchmark Wing

    Stanford, Bret / Jacobson, Kevin E. / Massey, Steven | AIAA | 2020


    Unsteady pressure distributions around an aeroelastic NACA 0012 wing in transonic flows

    Finaish, Fathi / Frigerio, Jacopo / Bennett, Robert | AIAA | 1995


    NACA 0012 aerofoil in an oscillating transonic free-stream

    Fernie, R. / Babinsky, H. | AIAA | 2002