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sysprob10 - Lab 10 Wing Structural Analysis and Bending...

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Unformatted text preview: Lab 10 Wing Structural Analysis and Bending Test Unified Engineering 20 Apr 06 Learning Objectives Structural analysis of a foam wing. Benchtop bending test of wing, and comparison with analysis. Procedure Correct any calculation errors which occurred in the wing design in previous Labs. Cut your wing on the AA CNC foam cutter. Save the scrap foam beds which remain. Measure the actual root and tip chords and thicknesses c r , c t , t r , t t of the airfoil. Their ratios will not correspond exactly to your and , because the foam cutting isnt perfect. For multi-panel wings, measure the thicknesses at the two ends of each panel. Perform the spreadsheet structural analysis of your wing, per the Lab 10 notes. Use a spanwise bending inertia distribution I ( y ) = 0 . 037 c t 3 corresponding to your measured chords and thicknesses. For a simple taper, the local c , t would be c ( y ) = c r + ( c t c r ) 2 y/b t ( y ) = t r + ( t t t r ) 2 y/b...
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