Nonstationary pressure distributions and aerodynamic derivatives are presented for a NACA 64A006 airfoil with oscillating flap in Mach number range from 0.5 to 1.00. Values for the reduced frequency between 0 and 0.39 are included. The results supersede a part of the earlier results given in NLR report TR F253. (Author)


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    Title :

    Results of Pressure Measurements on an Airfoil with Oscillating Flap in Two-Dimensional High Subsonic and Transonic Flow (Zero Incidence and Zero Mean Flap Position)


    Contributors:
    H. Tijdeman (author) / P. Schippers (author)

    Publication date :

    1973


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English