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Flutter Sensitivity to Boundary Layer Thickness, Structural Damping, and Static Pressure Differential for a Shuttle Tile Overlay Repair ConceptThis paper examines the aeroelastic stability of an on-orbit installable Space Shuttle patch panel. CFD flutter solutions were obtained for thick and thin boundary layers at a free stream Mach number of 2.0 and several Mach numbers near sonic speed. The effect of structural damping on these flutter solutions was also examined, and the effect of structural nonlinearities associated with in-plane forces in the panel was considered on the worst case linear flutter solution. The results of the study indicated that adequate flutter margins exist for the panel at the Mach numbers examined. The addition of structural damping improved flutter margins as did the inclusion of nonlinear effects associated with a static pressure difference across the panel.
Document ID
20090014788
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Scott, Robert C. (NASA Langley Research Center Hampton, VA, United States)
Bartels, Robert E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
April 1, 2009
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2009-215708
LF99-8048
L-19552
Funding Number(s)
WBS: WBS 377816.06.02.03.20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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