Author:
Baghdad Mohammed,Nehmar Abdelkader,Ouadha Ahmed
Abstract
The objective of the present study is to carry out a numerical study of the flow around a NACA0021 modified wing by the incorporation of sinusoidal tubercles on its leading edge at a Reynolds number equal to 225,000. The SST k-ω turbulence model is used as closure to the incompressible governing equations. Runs have been performed for several attack angles. Results show that for lower angles of attack, tubercles reduce the drag coefficient with a slight increase in lift.
Reference49 articles.
1. Fish F.E., Battle J.M., J. Morphology, 225 (1995)
2. Fish F.E., New Hampshire, 1999
3. Hansen K.L., Effect of leading edge tubercles on airfoil performance. Ph.D. Dissertation, The School of Mechanical Engineering, The University of Adelaide, South Australia (2012)
4. Miklosovic D.S., Murray M.M., Howle L.E., Fish F.E., Physics of Fluids, 16 (2004)
5. Miklosovic D.S., Murray M.M., Journal of Aircraft, 44 (2007)