Effect of Wing Damage on Aeroelastic Behavior
Lunch and beverages will be served
Friday, December 7, 2007 - 12:00pm
Hudson Hall Room 216
Elizabeth Irish firstname.lastname@example.org or Justin Jaworski email@example.com
Semester & Year:
Aeroelasticity addresses the phenomena that arise due to the interactions among aerodynamic, inertial, and elastic forces. The inertial and elastic forces are found from modeling the wing structure using the finite element method. The finite element method has been validated experimentally and shown to determine accurately the structural properties of a thin, elastic isotropic plate with a hole (damage) for various materials and geometries. The aerodynamic theory used in this work is developed from potential flow theory. The doublet lattice method as developed by Dr. Edward Albano and Dr. William Rodden in the 1960's models the aerodynamics. Matching the structural and aerodynamic geometries can be achieved by various techniques; here, a least square polynomial curve fit is applied to the structural deflections of a given mode. The deflections are used in calculating the downwash, which is then used in the aerodynamic model. Future aeroelastic studies will incorporate the V-g method for flutter prediction using the equations of motions derived through Lagrange’s equation. The goal here is to develop a theoretical model that correlates well with an experimental wind tunnel model in order to develop a greater confidence in aeroelastic design methods for damaged wings.