Viscous drag reduction using riblets on a swept wing

Sundaram, S and Vishwanath, PR and Subhaschandar, N (1999) Viscous drag reduction using riblets on a swept wing. AIAA Journal, 37 (7). pp. 851-856. ISSN 0001-1452

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Results of viscous drag reduction using 3M riblets on a swept wing with a general aviation wing (GAV)(2) airfoil section at low speeds are presented. The tests, made at a chord Reynolds number of 0.75 x 10 exp 6, covered an incidence range of 0-6 deg. Measurements consisted of surface-pressure distributions and total drag using wake survey over the range of incidence covered; in addition, mean velocity, streamwise turbulence intensity, and Reynolds shear-stress profiles in the boundary layer were measured just ahead of the trailing edge at zero incidence. 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 percent at zero incidence, which decreased progressively to about 1 percent at an incidence of 6 deg. 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 in the boundary layer on the wing's upper surface have been observed in the presence of riblets, as in two-dimensional flows.

Item Type: Article
Additional Information: Copyright for this article belongs to AIAA
Uncontrolled Keywords: Drag(hindrance);Aircraft wings;Boundary Layer; Turbulence;Swept wings;Aeronautics;Reynolds number;Airfoils
Subjects: AERONAUTICS > Aerodynamics
Depositing User: M/S ICAST NAL
Date Deposited: 08 Mar 2010
Last Modified: 24 May 2010 04:21

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