Consideration is restricted to the stressing of blades in steady flight. The loading actions on a blade are analyzed into two components; a transverse load system which tends to bend the blade, and an extensional system which tends to reduce this bending. The equation of elastic equilibrium of a blade under the action of these loads is then formulated. “Type solutions” are constructed which satisfy this equation and the appropriate end conditions. This method of attack provides a rapid means of estimating the blade stresses and is effective in demonstrating the influence of design parameters.
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