A Note on the Supersonic Panel Flutter of Oblique Clamped Plates

Abstract

Summary and IntroductionRecently, the effect of sweepback on the boundaries of supersonic panel flutter was studied in Ref. (1), (2) and (3), all of them dealing with rectangular plates.The present note considers the problem of panel flutter boundary of plates in the shape of a parallelogram with all edges clamped.It is assumed that Ackeret's theory of linearised two-dimensional supersonic aerodynamic loading gives an adequate approximation to the air forces for high Mach numbers.The criterion of instability is the coalescence of frequencies.A four-mode solution was obtained by means of Galerkin's method using first two streamwise and spanwise deflection modes. The results are represented in the form of diagrams for different aspect ratios(a/b)and sweep angles(ϕ).