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dc.contributor.authorP.B. Martin
dc.contributor.authorK.W. McAlister
dc.contributor.authorChandrasekhara, M.S.,
dc.contributor.authorW. Geissler
dc.date.accessioned2016-10-03T17:55:25Z
dc.date.available2016-10-03T17:55:25Z
dc.date.issued2003
dc.identifier.citationP.B. Martin, K.W. McAlister, M.S. Chandrasekhara, and W. Geissler, "Dynamic Stall Measurements and Computations for a VR-12 Airfoil with a Variable Droop Leading Edge", presented at the AHS Forum 59, Phoenix, AZ, May 6-8, 2003, American Helicopter Society "Best Paper Award" for 2003.
dc.identifier.urihttp://hdl.handle.net/10945/50038
dc.descriptionpresented at the AHS Forum 59, Phoenix, AZ, May 6-8, 2003, American Helicopter Society "Best Paper Award" for 2003.en_US
dc.description.abstractHigh density-altitude operations of helicopters with advanced performance and maneuver capabilities have lead to fundamental research on active high-lift system concepts for rotor blades. The requirement for this type of system was to improve the sectional lift-to-drag ratio by alleviating dynamic stall on the retreating blade while simultaneously reducing the transonic drag rise of the advancing blade. Both measured and computational results showed that a Variable Droop Leading Edge (VDLE) airfoil is a viable concept for application to a rotor high-lift system. Results are presented for a series of 2D compressible dynamic stall wind tunnel tests with supporting CFD results for selected test cases. These measurements and computations show a dramatic decrease in the drag and pitching moment associated with severe dynamic stall when the VDLE concept is applied to the Boeing VR-12 airfoil. Test results also show an elimination of the negative pitch damping observed in the baseline moment hysteresis curves.
dc.titleDynamic Stall Measurements and Computations for a VR-12 Airfoil with a Variable Droop Leading Edgeen_US


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