Dynamic Stall Alleviation using a Deformable Leading Edge Concept - A Numerical Study
Author
Sahin, Mehmet
Sankar, Lakshmi N.
Chandrasekhara, M.S.
Tung, Chee
Date
2000Metadata
Show full item recordAbstract
Dynamic stall calculations were carried out for an
airfoil with a deformed leading edge shape at a freestream
Mach number of 0.3. The surface deformations were done
about a baseline NACA 0012 airfoil, effectively increasing
the airfoil leading edge radius and thickness at high angles
of attack. It was found that the DDLE airfoil had a slightly
dynamic stall behavior compared to the baseline NACA
0012 airfoil. In particular, the lift, drag and pitching
moment hysteresis loops were milder for the DDLE airfoil
compared to the baseline airfoil. It was also found that a
static shape that corresponds to the thickest deformed shape
performed just as well as the DDLE shape, indicating that
the shape itself, and not its time rate of change, was the
reason for the improved performance. At higher Mach
numbers around 0.4, the DDLE shape exhibited a strong
dynamic stall triggered by a shock induced separation,
offsetting any benefit from the change in the shape of the
airfoil. Additional work is needed on the development of
DDLE shapes that will perform well at higher speeds.
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.2000-520
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
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