For the same example, take the cut at $12$ section and move $s$ in cew. Calculate:

$qb$ for all segments $(21,16,65,54,43,32)$

$qs,0$

Final q for all segments above

You can start from qb equation in slide $14eq($ii$)$

Please draw qb and qs on the section so you can indicate the direction

Example $21\mathrm{.}2$

The cantilever beam shown in Fig. $21\mathrm{.}6$ is uniformly tapered along its length in both $x$ and $y$ directions and carries a load of $100kN$ at its free end. Calculate the forces in the booms and the shear flow distribution in the walls at a section $2m$ from the built$-$in end if the booms resist all the direct stresses while the walls are effective only in shear. Each corner boom has a crosssectional area of $900m{m}^2$ while both central booms have crosssectional areas of $1200m{m}^2$ after full idealization

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I give you the example and slide $14,$ please solution step by step

Subject name aircrafts structure