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m10_ps04_spring04

# m10_ps04_spring04 - Unied Engineering Str-Mat Fluids...

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Unified Engineering Spring 2004 Str-Mat / Fluids Problem M10/Fxx Consider two wings with the same span b = 2 m , and average chord c avg = 0 . 25 m, but different taper ratios: Constant chord ( c r = 0 . 250 m, c t = 0 . 250 m, r = 1 . 0) Straight taper ( c r = 0 . 333 m, c t = 0 . 167 m, r = 0 . 5) Constant airfoil thickness/chord ratio κ = 0 . 08 everywhere. Assume local loading q ( y ) is proportional to chord c ( y ). Total load on half-wing is F = 10 N (15 oz gross weight at 5 g’s). For each wing . . . a) Determine q ( y ) , S ( y ) , M ( y ) b) Assuming load is carried by top and bottom sparcaps with separation equal to local h ( y ) = κc ( y ), determine sparcap load ± P ( y ). c) Assuming max permissible sparcap stress (1 ksi = 7 MPa for balsa), calculate minimum cap area A ( y ). Assuming balsa density of
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