Static and Dynamic Aeroelasticity

Abstract Aeroelasticity is concerned with the consequences created by interactions among aerodynamic forces, structural deformation, and motion of aerodynamic and hydrodynamic surfaces. Aeroelasticity has four primary effects: (i) lift redistribution that changes external loads; (ii) changes in aircraft trim and dynamic response; (iii) control effectiveness, including aileron reversal, which limits maneuverability; and (iv) aircraft structural dynamic response, in particular buffeting and flutter. A simple model is used to explain some of these effects. Aeroelastic effects have plagued aircraft from the beginning of flight, sometimes delaying technology transition. Early designs suffered from tail flutter and aileron‐wing flutter that led to in‐flight aircraft destruction. Flutter is a self‐excited structural dynamic instability that occurs when, at high speeds, wing or tail surface vibration extracts energy from the airstream. Today, aircraft development includes extensive, expensive analysis and testing to provide safe operation and prevent flutter. Solutions to aeroelastic problems nearly always include adding structural weight. Aeroelastic structural stiffness tailoring and active aeroservoelastic control are alternative remediation and exploitation methods. These efforts have led to modern designs such as the X‐29 research aircraft and the FA‐18 Active Aeroelastic Wing. A list of standard textbooks and major references is included.