Investigation on sound field model of propeller aircraft - the effect of vibrating fuselage boundary

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Investigation on sound field model of propeller aircraft - the effect of vibrating fuselage boundary

Wang, T.Q. / Zhou, S.

The sound field model with multiple propeller noise sources and finite fuselage boundary developed for the prediction of propeller aircraft noise in reference (1) has been improved to take into consideration the effects of vibrating fuselage boundary. The model could be used to solve acoustic-elastic problems, such as calculating the added modal mass and loss factor induced by the interaction between the external sound field and fuselage structure. For demonstration of its application the intermodal coupling coefficients of a scaled fuselage model have been ascertained. For verification purposes the sound field radiated by a sphere with a cyclically vibrating surface has been calculated by this model. The results are coincident with those yielded by an analytical method. The calculation of sound power radiated by a static sphere source gives the model and the numerical method additional proof of their validity. It illustrates that the improved model and its numerical method are valid, reasonable and useful.