Compressible Dynamic Stall Control Using a Shape Adaptive Airfoil
MetadataShow full item record
Compressible dynamic stall control using a dynamically deforming leading edge airfoil is reported. The technique uses real-time leading edge shape adaptation to manipulate the local adverse pressure gradient over an oscillating airfoil. This produces attached leading edge flow at all angles of attack in the cycle. The shape change schedule is tailored to achieve the “right” airfoil shape through the dynamic stall regime by rounding the nose on the upstroke and sharpening it on the downstroke. The method exploits the favorable effects of shape adaptation on the potential flow to modify the pressure field and maintain the peak vorticity level below the critical level at which the dynamic stall vortex develops. The sensitivity of the flow to rate of nose curvature change and the angle of attack at which the initiation occurs has been investigated.
AIAA Paper 99-0650 Reno, NV, Jan. 1999 (Under Review for AIAA Journal).
Showing items related by title, author, creator and subject.
Lin, Kyle Y.; Atkinson, Michael; Glazebrook, Kevin D. (2013-08-12);This paper considers a patrol problem, where a patroller traverses a graph through edges to detect potential attacks at nodes. Attackers arrive at each node according to independent Poisson processes and take a random ...
Chandrasekhara, M.S.; Wilder, M.C.; Carr, L.W. ;The challenging task of properly tripping the boundary layer of a leading-edge-stalling airfoil experiencing compressible dynamic stall at Reynolds numbers between 3.6 X 10⁵ and 8.1 X 10⁵ has been addressed. Real-time ...
Murray, Jessica L. (Monterey, California. Naval Postgraduate School, 2003-06);A dynamic subversion attack on the Windows XP Embedded operating system is demonstrated to raise awareness in developers and consumers of the risk of subversion in commercial operating systems that may be safety critical. ...