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Until recently, correlation between theory and experiment for flutter of panels stressed to the verge of buckling has not been achieved because of the theoretical prediction of anomalous zero dynamic pressure flutter points. However, a recent linear flutter analysis (NASA TN D-4990) which includes hysteretic structural damping on the bending terms of the flutter equation eliminates the anomalous zero dynamic pressure flutter points and yields good agreement. Thus, it appears that empirical flutter envelopes now used in design, which in many instances are extremely unconservative, can be replaced by design procedures with a more rigorous analytical basis. Toward this end, this paper develops and presents design charts for biaxially loaded isotropic panels on the verge of buckling for typical values of structural damping. Use of these charts permits conservative panel design for wide ranges of panel length-width ratio, in-plane stress ratio, and edge rotational restraint. NomenclatureA = (a/6) 2 fe -2] a = panel length b = panel width c = freestream speed of sound D = flexural stiffness of isotropic panel Di = />*/(

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