Unsteady unified hypersonic/supersonic method for aeroelastic applications including wave/shock interaction

A unified unsteady hypersonic/supersonic method using perturbed Euler characteristics (PEC) has been developed for the treatment of stability derivatives and panel flutter of wedgelike profiles. The present PEC method is valid for all supersonic Mach numbers, ranging from the low supersonic shock-attached limit to the Newtonian limit, in the complete frequency range, and for arbitrary body thickness so long as the bow shock remains attached to the body apex. The unsteady lifts, moments, and stability derivatives for oscillating wedge profiles, an oscillating leading-edge flap, and the related panel flutter problem are studied. Our computed results are found to differ with those of piston theory and linear potential theory in their invalid regions as expected. The essential feature of the PEC method lies in that it can fully account for the unsteady Mach wave/shock wave interaction and, hence, the rotationality and thickness effects. In view of its exactness, in terms of the characteristic formulation, and its ease of application, the present (PEC) method should be a promising method for panel flutter applications to hypersonic vehicles such as NASP.