Results are presented of unsteady separated flow computations using the LTRAN2-NLR code (low-frequency transonic small perturbation theory) coupled in strong interaction with Green's lag-entrainment method for a steady turbulent boundary layer. Computations of shock-induced separation have been carried out for a supercritical airfoil oscillating in pitch and for the NACA 0012 airfoil at a transient change of angle of attack.


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    Title :

    Computations of Separated Subsonic and Transonic Flow about Airfoils in Unsteady Motion


    Contributors:
    R. Houwink (author)

    Publication date :

    1984


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English