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dc.contributor.authorChandrasekhara, M.S.
dc.contributor.authorM.C.Wilder
dc.contributor.authorL.W.Carr
dc.date.accessioned2016-10-03T17:55:24Z
dc.date.available2016-10-03T17:55:24Z
dc.date.issued1993
dc.identifier.citationM.S. Chandrasekhara, M.C. Wilder and L.W. Carr, "Transition Effects on Compressible Dynamic Stall of Transiently Pitching Airfoils", AIAA Paper 93-2978 Orlando, FL, Jul. 6-9, 1993.
dc.identifier.urihttp://hdl.handle.net/10945/50033
dc.descriptionAIAA Paper 93-2978 Orlando, FL, Jul. 6-9, 1993.en_US
dc.description.abstractExperimental results and analysis of the effects of boundary layer tripping on dynamic stall of a transiently pitching airfoil are presented. At low Mach numbers, the tripped airfoil exhibits qualitative similarity with the behavior of the untripped airfoil. However, the local supersonic flow at Mach numbers greater than 0.3 is significantly modified by the trip leading to vastly different shock/boundary layer interactions, dynamic stall onset and vortex formation angles. The formation of the laminar separation bubble is found to have a favorable influence in delaying dynamic stall on the untripped airfoil flow. In both Mach number regimes, the tripped flow actually stalls at slightly lower angles of attack. Further experimentation with three trips on an oscillating airfoil showed that the dynamic stall process is very sensitive to the state of the turbulence in the boundary layer. This sensitivity points to a need for finer turbulence modeling techniques for use in dynamic stall computations.
dc.titleTransition Effects on Compressible Dynamic Stall of Transiently Pitching Airfoilsen_US
dc.description.funderAFOSR grant MIPR-93-0003
dc.description.funderARO-MIPR-125-93


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