Studies on Drag Reduction Using Riblets on a Infinite Swept Wing

Sundaram, S and Viswanath, PR and Subaschandra, N (1998) Studies on Drag Reduction Using Riblets on a Infinite Swept Wing. Technical Report. National Aerospace Laboratories, Bangalore, India.

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    Abstract

    Results of viscous drag reduction using 3M riblets on an infinite swept wing with GAW(2) airfoil section at low speeds are presented. The tests, made at a chord Reynolds number of 0.75x106, covered an incidence range of 0 to 6xB0;. Measurements made consisted of surface pressure distributions, total drag using wake survey method and streamwise turbulence intensity and Reynolds shear stress profiles just ahead of the trailing edge. Surface flow patterns on the wing were obtained using an oil flow technique employing Titanium dioxide as pigment. The results showed viscous drag reduction of about 8% at zero incidence which decrease progressively to about 1 % at an incidence of 6xB0;. The fall in riblet effectiveness appears to be a result of significant riblet yaw angle effects observed at higher incidence. Some reduction in the turbulence intensity and Reynolds shear stress near the wall have been observed in the presence of riblets as in two-dimensional flows.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Riblets;Swept wing;Drag reduction;GAW airfoil
    Subjects: AERONAUTICS > Aircraft Design, Testing & Performance
    AERONAUTICS > Aerodynamics
    Division/Department: Experimental Aerodynamics Division, Experimental Aerodynamics Division, Experimental Aerodynamics Division
    Depositing User: Mrs Neetu Chandra
    Date Deposited: 09 May 2006
    Last Modified: 24 May 2010 09:41
    URI: http://nal-ir.nal.res.in/id/eprint/1301

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