Some experiments on the flutter of sweptback cantilever wing models at Mach number 1.3

Flutter tests of sweptback cantilever wing models have been made in a small intermittent two-dimensional supersonic tunnel where the testing technique involved changing the structural parameters so that the models would flutter at the tunnel design Mach number of 1.3.Data for 21 models covering sweep angles from 30° to 600 and with varYing parameters are included.No attempt is made to correlate the data with analytical developments.However, reference values of flutter speed, obtained with a swept-wing flutter analysis based on two-dimensional incompressible flow, are compsxed with the experimental flutter speed in order to unify the results.The incompressible-flow flutter theory appears very conservative for the 30° to 45° sweptback models and is in reasonable agreement for the 600 sweptback models at Mach number 1.3.Caution should be observed in extrapolating these data to conditions other than those covered in the tests.