Abstract
A numerical and experimental study of the flow near a standard civil-aircraft model at high angles of attack in the range from 0 to 90° and at subsonic velocities of the oncoming flow has been carried out. The experiments were performed in the T-105 wind tunnel of TsAGI. The calculations were carried out within the framework of solving the Reynolds-averaged Navier–Stokes equations. A comparison of the calculated and experimental integral characteristics showed a good agreement with an accuracy sufficient for practice. Physical features of the flow and their influence on the aerodynamic characteristics of a stationary model at high angles of attack, as well as in the regime of rotation of the model with a constant angular velocity, are revealed.
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This study (numerical simulation) was supported by the Russian Science Foundation (Grant No. 21-19-00659, https://rscf.ru/en/project/21-19-00659/).
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Voevodin, A.V., Efremov, A.A. & Soudakov, V.G. Numerical and experimental study of the aerodynamics of a civil-aircraft model at high angles of attack and during rotation. Thermophys. Aeromech. 30, 1–12 (2023). https://doi.org/10.1134/S0869864323010018
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DOI: https://doi.org/10.1134/S0869864323010018