Elastic wing response’s to an incoming gust
DOI:
https://doi.org/10.1260/175095407781421577Abstract
The behavior of thin elastic blade and wing subjected to a travelingdisturbance is considered. The blade response to an incoming gust ispredicted, then the pressure around the blade is coupled to the far fieldpressure in order to predict the intensity of acoustic radiation as well as theacoustic wave propagation in far field. The effect of the elasticity of theblade on the acoustic wave is predicted. The blade vibration induced bylanding acoustic wave is investigated. The two dimensions inviscid flowaerodynamic theorem associated with the strip theorem are used to modelthe flow around the elastic thin wing. Bernoulli-Euler theorem are used inorder to describe the wing motion. The fluid and the wing motions arecoupled via the boundaries condition at the blade surface. The incominggust considered here is a monochromatic wave traveling with a givenspeed. The problem formulation leads to a forced well known aeroelasticityFung equation. The eigenvalue of the homogeneous part are computedand a formal solution of the forced equation is obtained.The behavior of thin elastic blade and wing subjected to a travelingdisturbance is considered. The blade response to an incoming gust ispredicted, then the pressure around the blade is coupled to the far fieldpressure in order to predict the intensity of acoustic radiation as well as theacoustic wave propagation in far field. The effect of the elasticity of theblade on the acoustic wave is predicted. The blade vibration induced bylanding acoustic wave is investigated. The two dimensions inviscid flowaerodynamic theorem associated with the strip theorem are used to modelthe flow around the elastic thin wing. Bernoulli-Euler theorem are used inorder to describe the wing motion. The fluid and the wing motions arecoupled via the boundaries condition at the blade surface. The incominggust considered here is a monochromatic wave traveling with a givenspeed. The problem formulation leads to a forced well known aeroelasticityFung equation. The eigenvalue of the homogeneous part are computedand a formal solution of the forced equation is obtained
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