m18_ps05_spring04

m18_ps05_spring04 - orientated perpendicular to the maximum...

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Unified Engineering Spring 2004 Problem M18: Aluminum 7075-T6 has a fracture toughness of 24 MPa√m. As part of the design for damage tolerance requirements for the wing skin component you analyzed in M17 it is required that the critical crack size be greater than 5 mm (so that it can be detected by non destructive evaluation (NDE) techniques). Assume that the worst case is for a crack
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Unformatted text preview: orientated perpendicular to the maximum tensile stress component. Verify that the thicknesses you specified in M17 will meet the damage tolerance requirement. If they do not, then specify a new value of the thickness that will allow the panel to meet both the strength and the damage tolerance requirements....
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This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.

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