Aerospace Engineering > GATE 2017 > Beam Deflection
An aircraft wing is idealized as a cantilever beam of constant width and length I with a tip mass of weight W (Newtons) and has a uniformly distributed loading of qo (Newtons/m) as shown in the figure. Flexural rigidity =EI and qo l=10 W.
The upward deflection of the tip of the aircraft wing under the given loading can be expressed as:
δ=k Wl3/EI
The value of k is _______ (in three decimal places).
δ=k Wl3/EI
The value of k is _______ (in three decimal places).
Correct : 0.910 to 0.920
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