Article thumbnail

Drag Reduction Due to Riblets on a NACA 0012 Airfoil at Higher Angles of attack

By N Subaschandar, Kumar Rajeev and S Sundaram


Previous investigations of viscous drag reduction due to riblets on a NACA 0012 by Sundaram et al 1 '2 has been extended to higher angles of attack. Tests were made at a freestream velocity of 30 m / s and angle of attack ((X) ranging from 8xB0; to 12xB0;. 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 a = 5xB0;, decreased rapidly with a further increase in a; there was13; virtually no drag reduction at a = 12xB0;

Topics: Aerodynamics
Publisher: National Aerospace Laboratories
Year: 1995
OAI identifier:
Provided by: NAL-IR
Download PDF:
Sorry, we are unable to provide the full text but you may find it at the following location(s):
  • (external link)
  • (external link)
  • (external link)
  • Suggested articles

    To submit an update or takedown request for this paper, please submit an Update/Correction/Removal Request.