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Drag reduction due to riblets on a NACA 0012 airfoil at higher angles of attack

N. Subaschandar, Kumar Rajeev, Shivshankar Sundaram

Open publisher page 9 citations

Abstract

Previous investigations of viscous drag reduction due to riblets on a NACA 0012 by Sundaram et a1 has been extended to higher angles of attack. Tests were made at a freestream velocity of 30 m/s and angle of attack (&) ranging from 8 to 12. Total airfoil-drag was determined from wake survey while pressure drag was obtained by integrating surface pressure distributions on the model. Skin friction drag was estimated from the difference between total and pressure drag. Results showed that both total and skin friction drag reduction which were found to be about 13% and 15% respectively at cC =6 , decreased rapidly with a further increase in, there was virtually no drag reduction at cC= 12:

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What this paper is about

Previous investigations of viscous drag reduction due to riblets on a NACA 0012 by Sundaram et a1 has been extended to higher angles of attack. Tests were made at a freestream velocity of 30 m/s and angle of attack (&) ranging from 8 to 12. Total airfoil-drag was determined from wake survey while pressure drag was obtained by integrating surface pressure distributions on the model. Skin friction drag was estimated from the difference between total and pressure drag. Results showed that both total and skin friction drag reduction which were found to be about 13% and 15% respectively at cC =6 , decreased rapidly with a further increase in, there was virtually no drag reduction at cC= 12:

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OpenAlex reports 9 citations for this work. Citation counts describe recorded attention and do not establish research quality.

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Available abstract

Previous investigations of viscous drag reduction due to riblets on a NACA 0012 by Sundaram et a1 has been extended to higher angles of attack. Tests were made at a freestream velocity of 30 m/s and angle of attack (&) ranging from 8 to 12. Total airfoil-drag was determined from wake survey while pressure drag was obtained by integrating surface pressure distributions on the model. Skin friction drag was estimated from the difference between total and pressure drag. Results showed that both total and skin friction drag reduction which were found to be about 13% and 15% respectively at cC =6 , decreased rapidly with a further increase in, there was virtually no drag reduction at cC= 12:

Key concepts: Drag, NACA airfoil, Airfoil, Parasitic drag, Drag divergence Mach number, Freestream, Zero-lift drag coefficient, Lift-induced drag

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