Presentation Title

Nonlinear Aeroelastic Analysis

Faculty Mentor

Michael Butros, Kurt Kloesel

Start Date

18-11-2017 10:00 AM

End Date

18-11-2017 10:15 AM

Location

9-285

Session

Physical Sciences 2

Type of Presentation

Oral Talk

Subject Area

physical_mathematical_sciences

Abstract

The accurate prediction of aeroelastic flutter and related phenomena are of major importance during the design phase of any aircraft. The use of an accurate computational model to predict when flutter occurs can save many hours of wind tunnel testing, confirm the structural integrity of the airframe, and ensure safety for the pilot when operating within the intended flight envelope. Additionally, an accurate computational model can aid in back-checking the fidelity of wind tunnel test data. Linear aeroelasticity has been the predominant method for modeling and predicting flutter and other aeroelastic phenomena for decades. However it can be potentially insufficient in certain cases, for example, when an aircraft has a highly flexible structure. Nonlinear methods are needed to account for the structural nonlinearities associated with deformation possible with highly flexible wings. Similarly, aerodynamic nonlinearities can pose problems even in more rigid aircraft structures. This project aims to utilize MATLAB to evaluate nonlinear flutter prediction methods, namely bifurcations and potentially Limit Cycle Oscillations (LCO), to analyze the aeroelastic behavior of simple wings with structural nonlinearities.

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Nov 18th, 10:00 AM Nov 18th, 10:15 AM

Nonlinear Aeroelastic Analysis

9-285

The accurate prediction of aeroelastic flutter and related phenomena are of major importance during the design phase of any aircraft. The use of an accurate computational model to predict when flutter occurs can save many hours of wind tunnel testing, confirm the structural integrity of the airframe, and ensure safety for the pilot when operating within the intended flight envelope. Additionally, an accurate computational model can aid in back-checking the fidelity of wind tunnel test data. Linear aeroelasticity has been the predominant method for modeling and predicting flutter and other aeroelastic phenomena for decades. However it can be potentially insufficient in certain cases, for example, when an aircraft has a highly flexible structure. Nonlinear methods are needed to account for the structural nonlinearities associated with deformation possible with highly flexible wings. Similarly, aerodynamic nonlinearities can pose problems even in more rigid aircraft structures. This project aims to utilize MATLAB to evaluate nonlinear flutter prediction methods, namely bifurcations and potentially Limit Cycle Oscillations (LCO), to analyze the aeroelastic behavior of simple wings with structural nonlinearities.