The paper is concerned with the aerodynamic performance of a low aspect ratio wing with symmetric leading edge vortex generators installed on its leading edge. The leading edge vortex generators invented at National Aviation University have proven their ability to improve aerodynamic performance as well as stability and control characteristics at high angles of attack in the framework of wind tunnel testing. In this work, the Computational Fluid Dynamics methods are employed to investigate aerodynamic features of a vortex flow around a wing and its impact on local and global performance. The ONERA M6 wing geometry is used for the study. The regime corresponds to a compressible subsonic turbulent flow. Several configurations of the wing with vortex generators were created and investigated. The obtained results confirm a significantly improved aerodynamics performance at high angles of attack of the configurations with leading edge vortex generators compared to the baseline wing. An analysis of the flow field is presented demonstrating vortex paths and elimination of flow separation and recirculation in the regions of the wing where vortex generators are installed.


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    Titel :

    Numerical Investigation of Aerodynamic Performance of Low Aspect Ratio Wing with Leading Edge Vortex Generators


    Beteiligte:


    Erscheinungsdatum :

    19.10.2021


    Format / Umfang :

    2103932 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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