A study of the effects of fuselage and its boundary layer on propeller/prop-fan noise

摘要

A approach to study the boundary layer retraction of propeller/prop-fan aircraft by acoustic analogy is developed. ^The boundary refraction effect is modelled as quadrupole source distributed in the boundary layer, and the quadrupole source expression and its integration equation are derived which could be used to study the interaction between an incident sound wave and the fuselage boundary layer. ^Using this approach, the surface sound pressure distribution of a cylinder fuselage model with high velocity are calculated and the boundary layer effect is shown. ^(Author)