Dynamic Stall Alleviation using a Deformable Leading Edge Concept - A Numerical Study
Loading...
Authors
Sahin, Mehmet
Sankar, Lakshmi N.
Chandrasekhara, M.S.
Tung, Chee
Subjects
Advisors
Date of Issue
2000
Date
2000
Publisher
American Institute of Aeronautics and Astronautics Inc.
Language
Abstract
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.
Type
Conference Paper
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.2000-520
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
14 p.
Citation
Mehmet Sahin, Lakshmi Sankar, M. Chandrasekhara, and Chee Tung. "Dynamic stall alleviation using a deformable leading edge concept - A numerical study", 38th Aerospace Sciences Meeting and Exhibit, Aerospace Sciences Meetings, ()
Distribution Statement
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.