This chapter presents aeroelastic phenomena that occur at supersonic and hypersonic Mach numbers. Supersonic flight conditions are defined by M > 1 while hypersonic flow usually involves M > 4. There is a simple 2D quasi‐steady aerodynamic model that is valid throughout these two flow regimes, referred to as piston theory. The resulting aerodynamic models are nonlinear but the nonlinearity is weak so they are most often linearised. The chapter applies piston theory to two problems: a 2D airfoil oscillating in a supersonic/hypersonic flow and panel flutter. It shows a simplified model of an aeroelastic system prone to panel flutter, consisting of a simply supported plate of length a and thickness h. The buckling of a panel in supersonic flow is a complicated bifurcation phenomenon that originates at a Bogdanov‐Takens point at V = 0 and disappears either at a pitchfork point or at a fold.
High‐Speed Aeroelastic Nonlinearities
Introduction to Nonlinear Aeroelasticity ; 453-502
28.03.2017
50 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Aeroelastic behaviour of a wing including geometric nonlinearities
Online Contents | 2011
|Vibration Testing of Aeroelastic Structures Containing Geometric Stiffness Nonlinearities
British Library Conference Proceedings | 2013
|