Discrete element approach to flutter of skew panels with in-plane forces under yawed supersonic flow

Abstract

The flutter problem of skew panels, with inplane forces under yawed supersonic flow, has been considered in this paper through the application of matrix displacement methods. Necessary kinematically consistent aerodynamic influence coefficient matrices (AIC), which are applicable to yawed supersonic flows, have been developed and are employed in the formulation of the dynamic equations of motion. The results have also been compared with the other available results and the agreement is found satisfactory. This approach makes it possible to tackle flutter problems of panels with practically any boundary condition including13; cut-outs if any, and subjected to thermal or other midplane forces.