Aeroelastic Analysis on Wing Structure Using Immersed Boundary Method

摘要

Flutter of airplane's wing is a critical issue determining reliability of aircraft. Flutter phenomenon is the result of fluid-structure interaction and is usually involved with complicated phenomena such as shock wave-boundary layer interaction, flow separation, and nonlinear limited cycle oscillation. Accurate prediction of flutter is very challenging due to perplexing physical phenomena and requires large amount of computation. In this paper, a developed code based on immersed boundary method (IBM) was realized to predict aeroelastic response and characteristic parameters of the wing structure. There were two rectangular and two trapezoid 3D-shapes of wing; each 3D-shape of wing had NACA65A004 and supercritical airfoil, respectively. Results from IBM method were first analyzed to carry out behaviors of flow on and around airplane wings and then were compared with experimental results at low speed.