Wind tunnel tests were conducted to determine the effects of trailing edge modifications on the lift-to-drag ratio of a circulation controlled airfoil. The model was a 20 percent thick, five percent cambered, elliptical airfoil. The airfoil was modified in aft contour, blowing slot position, and blowing angle. A 1.5 inch splitter plate was mounted at the 99 percent chord for all tests. The tests were run at a Reynolds Number, based on model chord, of 741,000, while the angle of attack and blowing rate were varied during each test sequence.


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    Titel :

    A Wind Tunnel Study of the Effects of Trailing Edge Modifications on the Lift-Drag Ratio of a Circulation Controlled Airfoil


    Beteiligte:
    V. S. Oxford (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    68 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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