Abstract
A new formulation based on a Kinetic scheme namely the Kinetic Flux Vector Splitting scheme on Moving Grids(KFMG) for solving Euler equations has been developed for unsteady flow computations around oscillating bodies. The necessary grid movement has been achieved using spring analogy method on structured grids. An integrated Aeroelastic code has been developed by coupling the KFMG Euler solver with a 2-DOF structural dynamics model of an airfoil. Results obtained for steady and unsteady flows problems are compared with literature data and are discussed in detail. The aeroelastic response characteristics for NACA 64A006 airfoil undergoing pitch and plunge motions have been obtained using the present aeroelastic code. The well known ‘Transonic Dip’ phenomenon has been captured for NACA 64A006 airfoil using the present Computational Aeroelastic code.
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