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.
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Translated by K. Shakhlevich
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Ovchinnikov, V.V., Petrov, Y.V. & Filimonov, S.V. Calculation of the Aeroelastic Characteristics of a Wing during Vibrations in a Subsonic Flow by the Discrete Singularity Method. Russ. Metall. 2020, 1070–1078 (2020). https://doi.org/10.1134/S0036029520100201
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DOI: https://doi.org/10.1134/S0036029520100201