Finite Wings in Compressible Flows

This chapter extends the aerodynamic panel methodPanel method solution for aeroelastic applications, presented in Chap.  4 , to compressible flows. After the introduction of the Green’s function for the wave equationWave equation, which includes the delay effects of flow compressibility, the boundary integral formulationBoundary Integral Equation Method (BIEM) for lifting wings in subsonic flight is derived and the BEMBoundary Element Method (BEM) approach is applied to determine the aerodynamic matrixAerodynamic matrix that contributes to the definition of the aeroelastic operator in compressible flows.