Abstract
In the present paper, approximate formulas are derived, based on the “fiber-stress” concept, for the combined influence of aerodynamic heating and initial twist on the torsional stiffness of a thin wing. Criteria are established for calculating the critical temperature difference between that of the edges and that of the mid-chord position, for preventing possible aeroelastic reversals or buckling. Formulas are valid for wings with large aspect ratios.
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