tmin = .0129 in. (minimum allowable skin thickness)
2. Consider the cylindrical section of a semi-monocoque fuselage. The fuselage is pressurized to 15 psi gauge. The 50-in diameter fuselage shell is stiffened by 10 identical stringers. All memebers are made of the same material having ult. normal strength of 40 ksi, and ult. shear strength of 20 ksi with Poisson's ratio of 0.3. Using the factors of safety of 1.2 in tension and 2 in shear and keeping the ratio of total stringer area to skin area at 15%, determine
(a) the minimum allowable thickness for the fuselage skin,
(b) the cross-sectional area of each stringer.
(a)tmin = .0188 in
(b)Ast = .044 sq. in.