Consider a Y$-$shaped spar having a thin$-$walled open cross$-$section, as shown below. The beam is made from a single material, and it is used to carry the bending loads of a fixed wing drone. The wall thickness, $t,$ is uniform and much smaller than the flange width, a$.$ The effective shear force acting at the cross$-$section can be resolved as acting vertically at a length of a$)$ to the right of the common joint. Such force introduces both bending and twisting to the wing.

a$)$ Determine the shear flow distribution over the cross section associated with the shear force Sy and sketch the results.

b$)$ What is the maximum shear stress on the cross section associated with the shear load? At what point is it found?

c$)$ Demonstrate that the shear force resultant inside the structure is equal to the externally applied force.

d$)$ How would you redesign the part to prevent the wing from twisting under the applied load.

$(-4)$

plz solve $1$st two oarpart correctly.