Abstract
A method to calculate the supersonic bendingtorsion flutter speed of cantilever plate wings of low aspect ratio is presented. The deflection mode is assumed in a double power series expansion of spanwise and chordwise variables, and the flutter determinant is derived with the aid of the principle of minimum potential energy of the dynamic problem. The chordwise variable is measured from the midchord line along the stream direction for swept-back wings. For the aerodynamic force, the piston theory including the effect of wing thickness is used. Numerical computation is carried out for a cantilever trapezoid tested at the National Aerospace Laboratory. It has been observed that the ten terms approximation yields a good result in comparison with the twenty terms approximation. It has been clarified that the effect of aerodynamic damping on the flutter speed is very small. Reasonable results are obtained in comparison with the experimental results. Furthermore the present method is extended to cantilever plates partially clamped at the root.
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