Flutter Phenomena Effected by The Aerodynamic Load

Abstract

Abstract: The basic aim of this project is to define and investigate the flutter condition which occur at the wing and fuselage of the aircraft structure or any flying aerofoil such as engine fins during flight under different conditions and high speeds where the flutter causes a vibration on the wing and fuselage of the aircraft structure also on the structure of the fins which leads to a high risk of structure failure , if these vibrations are not controlled . The project gives some method of calculating flutter also the project suggests some answers to this problem by giving an example on airfoil fins model during high velocity with the basic equations and data .

Keywords

• ar aspect ratio- b chord length mm c / a length mid thickness to radius ratio ( thickness ratio ) cd drag coefficient cl lift coefficient cm moment coefficient cn normal force coefficient mm feli e modules of elasticity n/m2 fb bending freque
• bt
• ct) influence coefficient αº angle of attack degree θ the instantaneous angular displacement degree μ mass of the blade gm σ logarithmic decrement mm w eigen frequency rad\sec p air density kg / m3