This chapter presents three major aeroelastic phenomena caused by separated flow at subsonic or incompressible airspeeds. It only uses semi‐empirical models of the aerodynamic nonlinearities and shows that such models can represent the real phenomena with reasonable accuracy. The complete phenomenon of periodic flow separation and re‐attachment due to body motion is known as dynamic stall. A vortex shed during dynamic stall is known as a Motion‐Induced Vortex (MIV) or Leading Edge Vortex (LEV) or Dynamic Stall Vortex (DSV). From an aeroelastic point of view, separated flow vortices can cause two types of phenomena: lock‐in, and limit cycle oscillations. The term 'stall flutter' is usually employed to denote a limit cycle oscillation of a streamlined aeroelastic structure during which the flow separates from and re‐attaches itself to the body periodically. Galloping also involves periodic separation and re‐attachment.
Low‐Speed Aerodynamic Nonlinearities
Introduction to Nonlinear Aeroelasticity ; 389-451
2017-03-28
63 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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