A comparative study of two airfoils at low Reynolds numbers using the transitional unsteady Reynolds-averaged Navier–Stokes shear-stress transport γ - R e θ model and the ANSYS CFX computational fluid dynamics suite is proposed. The NACA 0012 and Selig–Donovan 7003 airfoils were selected and exposed to chord-based Reynolds numbers ranging from 4.8 × 10 4 to 2.5 × 10 5 at angles of attack ranging from 0 to 8 deg. The adopted numerical model and setup were shown to accurately predict the main flow features. Specifically, both laminar separation without reattachment and laminar-separation-bubble flow modes were observed depending on the airfoil geometry and orientation, Reynolds number, and freestream-turbulence intensity. In general, with increasing angle of attack or Reynolds number, laminar-separation bubbles shrank and receded toward the leading edge while vortex-shedding periodicity and coherency degraded. In all cases, the Selig–Donovan 7003 proved of superior aerodynamic performance when compared to the NACA 0012, which was expected.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Low-Reynolds-Number Aerodynamic Performances of the NACA 0012 and Selig–Donovan 7003 Airfoils


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 50 , 1 ; 204-216


    Erscheinungsdatum :

    2013-01-08


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch