Suppose you have an aircraft fuselage with a radius of 40" to the midplane of an aluminum skin, which is 0.050" thick. the fuselage has 8 hat-section longerons, the first of which is at the top centerline of the fuselage, and longerons 2 thru 8 are each inside the skin and spaced 45o apart as you move clockwise around the fuselage. each longeron has an area of 0.5 in2 and a negligible moment of inertia, and the centroid of each longeron is located at rh=39" from the center of the fuselage. set your coordinate system at the center of the fuselage with x into the page, y acting positive left, and with positive z upward, then (a) sketch & dimension the fuselage cross section, and (b) calculate the effective area, zbar, and iy. (note: you can use the approximate relations a=2πrt & iy=πr3t for the thin skin portion).