Effect of Wingtip Devices on Transonic Aeroelastic Phenomenon of Fixed-wing Aircraft
Location
Statesboro Campus (Room 2054)
Document Type and Release Option
Thesis Presentation (Open Access)
Faculty Mentor
Dr. Marcel Ilie
Faculty Mentor Email
milie@georgiasouthern.edu
Presentation Year
2022
Start Date
16-11-2022 7:05 PM
End Date
16-11-2022 8:05 PM
Description
Aeroelastic phenomena encountered during flight have considerable effects on the aerodynamic characteristics of fixed-wing aircraft. Transonic aeroelastic phenomena are often characterized by unique flow features which have complex ramifications for aircraft in transonic flight. Computational study of high-speed aeroelastic phenomena requires a fully-coupled aeroelastic algorithm. Therefore, wings with and without wingtip devices will be studied with a computational finite volume method solver accompanied by a finite element method solver for the calculation of structural deformation. The computational model for the flow field is validated with experimental data. Modeled flight conditions include transonic flows with bordering subsonic and supersonic cases included for completeness. The freestream Mach number and presence of wingtip devices will influence the aerodynamic characteristics of the wing, its elastic deformation, and the incurred structural stresses. The consequences of aeroelastic effects on the near-wing flow field are studied by visualization flow field surrounding the wing. The impact of dynamic aeroelastic effects on the flow over the wing surface and shock-induced flow separation is studied by consideration of the dynamic pressure on the wing surfaces.
Academic Unit
Allen E. Paulson College of Engineering and Computing
Effect of Wingtip Devices on Transonic Aeroelastic Phenomenon of Fixed-wing Aircraft
Statesboro Campus (Room 2054)
Aeroelastic phenomena encountered during flight have considerable effects on the aerodynamic characteristics of fixed-wing aircraft. Transonic aeroelastic phenomena are often characterized by unique flow features which have complex ramifications for aircraft in transonic flight. Computational study of high-speed aeroelastic phenomena requires a fully-coupled aeroelastic algorithm. Therefore, wings with and without wingtip devices will be studied with a computational finite volume method solver accompanied by a finite element method solver for the calculation of structural deformation. The computational model for the flow field is validated with experimental data. Modeled flight conditions include transonic flows with bordering subsonic and supersonic cases included for completeness. The freestream Mach number and presence of wingtip devices will influence the aerodynamic characteristics of the wing, its elastic deformation, and the incurred structural stresses. The consequences of aeroelastic effects on the near-wing flow field are studied by visualization flow field surrounding the wing. The impact of dynamic aeroelastic effects on the flow over the wing surface and shock-induced flow separation is studied by consideration of the dynamic pressure on the wing surfaces.
