Abstract
The flutter tests of cantilever wings in a heated wind tunnel at Mach number of 4.75 and the comparison with calculated results are presented. Test pieces are stainless steel trapezoid flat plates. Flutter was observed in a certain time duration when the temperature difference was higher than the critical one at a thermally transient state. Temperature distribution of a wing surface was measured by thermocouples. Using this distribution, the critical value is calculated by the authors' method. Good agreement is seen between theory and experiment.
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