An ongoing numerical investigation of unsteady shock/boundary layer interaction on a 2-d supercritical airfoil in transonic flow is presented. Initially, the finitevolume URANS solver DLR-TAU is used to simulate self-sustained periodic shock oscillations well known as shock buffet. Next, emphasis is put on the fixed-point stability of the steady flow field below the shock buffet onset. Therefore the flow is perturbed in time with small sinusoidal deflections of the airfoil geometry and random impulses. With increasing angle of attack the mean flow is shown to develop a damped aerodynamic resonance, that degenerates finally towards self-amplification. The occurrence of the aerodynamic resonance is closely related to the development of shock-induced separation, accompanied by quasi-steady inverse shock motion.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    A numerical study on aerodynamic resonance in transonic separated flow


    Beteiligte:
    Nitzsche, Jens (Autor:in)

    Kongress:

    2009 ; Seattle, WA (USA)


    Erscheinungsdatum :

    2009


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Numerical Experiments on Aerodynamic Resonance in Transonic Airfoil Flow

    Nitzsche, Jens / Giepman, Rogier H. | Tema Archiv | 2013


    Transonic Unsteady Separated Flow over Profile

    Pafnutiev, V. / International Council of the Aeronautical Sciences | British Library Conference Proceedings | 2000


    Dynamic Mode Decomposition of a Separated Nozzle Flow with Transonic Resonance

    Lárusson, Ragnar / Andersson, Niklas / Östlund, Jan | AIAA | 2017



    Quasi-steady doublet-lattice correction for aerodynamic gust response prediction in attached and separated transonic flow

    Friedewald, Diliana / Thormann, Reik / Kaiser, Christoph et al. | Online Contents | 2017