Calculation of the Aeroelastic Characteristics of a Wing during Vibrations in a Subsonic Flow by the Discrete Singularity Method

Abstract

The problem of determining the total and generalized aerodynamic forces for an airplane wing during vibrations in a compressible flow with allowance for the real frequencies of its natural vibrations is considered. The need to develop operational numerical methods for solving the problem, which is reduced to a Neumann-type boundary problem for a scalar Helmholtz equation, is substantiated. The results of numerical calculations of the wing of the Yak-130 aircraft are presented.