A Collection of Technical Papers, Volume 2 |
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adhesive Advanced aerodynamic AIAA aileron aircraft alloy aluminum American analysis applied approach assumed bending bond buckling calculated compared composite compressive concepts configuration considered constant cost crack growth curve cycle damping determined developed direction displacement distribution Dynamics effect element energy Engineers equations evaluated experimental factor failure fatigue Figure flight flow flutter Force fracture frequency function given improved inch increase indicated initial integration length load lower material matrix maximum measured Mechanical method mode normal Note obtained occur panels parameters peak phase plate predicted presented pressure problem procedure properties range ratio reduced Reference representative response shear sheet shell shown shown in Figure shows skin solution specimens spectrum speed strain strength stress structural surface Table tensile theory thickness tion titanium values weight wing