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dc.contributor.authorSahin, Mehmet
dc.contributor.authorSankar, Lakshmi N.
dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorTung, Chee
dc.date2000
dc.date.accessioned2016-10-11T19:10:09Z
dc.date.available2016-10-11T19:10:09Z
dc.date.issued2000
dc.identifier.citationMehmet 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, ()
dc.identifier.urihttp://hdl.handle.net/10945/50219
dc.descriptionThe article of record as published may be found at http://dx.doi.org/10.2514/6.2000-520
dc.description.abstractDynamic 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.en_US
dc.format.extent14 p.en_US
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc.en_US
dc.rightsThis 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.en_US
dc.titleDynamic Stall Alleviation using a Deformable Leading Edge Concept - A Numerical Studyen_US
dc.typeConference Paperen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US


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