A composite rotor blade of an attack helicopter can be treated as a long slender beam having a 25ft length, a 1.7ft chord, and a uniform 250lb weight. During flight, the main rotor spins at 260rpm, where the lift and drag distributions vary with the square of the rotor speed. The centrifugal force varies with distance from the rotor center and the square of the rotor speed. Assume the blade mass axis is aligned with the blade quarter-axes. a.) Calculate load distributions ( p_(k),p_(y),p_(z),m_(v) m_(y),m_(z) ) in the coordinate axes. b.) Calculate the reactions at the blade fixed end. c.) Calculate the stress resultant distributions ( V_(x),V_(y),V_(z),M_(x),M_(y),M_(2)). d.) Plot the stress resultants. Label the blade root (fixed end) and