Relaminarization on swept leading edges under high-lift conditions 2004-99

Viswanath, PR and Mukund, R (2004) Relaminarization on swept leading edges under high-lift conditions 2004-99. In: 42nd AIAA Aerospace Sciences Meeting and Exhibit, 5-8 January 2004, Reno, Nevada.

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    Experiments were conducted to generate a wind13; tunnel data base on swept-wing relaminarization13; under high-lift conditions. Three swept wings with13; different airfoil sections and flaps were tested and13; measurements made consisted of surface pressure13; distributions and wall shear stress fluctuations in13; the leading edge zone. Measurements were made at13; a chord Reynolds number of 1.3x106 and model13; incidence was varied in the range 3xB0; to 18xB0; in13; discrete steps.13; Following attachment line transition, the turbulent13; boundary layer relaminarized under certain13; conditions due to the acceleration around the wing13; leading edge. Broad features of relaminarization13; and subsequent retransition are discussed based on13; wall shear stress fluctuation data. The present data13; set shows that relaminarization is likely if the13; (max) value of acceleration parameter, Ks (based13; on the streamwise velocity), is greater than about13; 3x10-6, and that much higher values of (max) Ks13; result in significant reduction of intermittency13; during relaminarization.13;

    Item Type: Conference or Workshop Item (Paper)
    Uncontrolled Keywords: Relaminarization;Accuracy of Measured Data;Streamwise Pressure and Acceleration13; Distributions
    Subjects: AERONAUTICS > Aeronautics (General)
    Division/Department: Experimental Aerodynamics Division, Experimental Aerodynamics Division
    Depositing User: Mr. N A
    Date Deposited: 27 Jan 2006
    Last Modified: 14 Oct 2015 16:03

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