E. A. Mitrukova, O. V. Mishchenkova, A. A. Chernova

SOME ASPECTS IN THE NUMERICAL SIMULATION OF THE AERODYNAMICS OF A NACA 0012 AIRFOIL

The paper discusses the numerical simulation of the aerodynamics of an airfoil at different angles of attack. Two approaches to determining the angle of attack are considered: by changing the position of the velocity vector of the oncoming flow and by changing the relative position of the flat airfoil. The value of the angle of attack varies in the range from −5 to +10°. Numerical simulation is performed with the openFoam package for solving continuum mechanics problems in the stationary setting based on finite volumes using the rhoSimpleFoam solver. The study results in the values of flow velocity and pressure, partially determined by the method of setting the angle of attack. A significant influence of the method of setting the angle of attack on the calculated aerodynamic coefficients is demonstrated. The mathematical correctness and numerical ambiguity of the considered approaches are assessed. A comparison among the drag coefficients, together with a qualitative analysis of the fields of physical quantities, shows incorrectness in determining the angle of attack by changing the position of the incoming flow velocity vector.

References:

1. Ladson, Ch.L. Effects of independent variation of Mach and Reynolds numbers on the low-speed aerodynamic characteristics of the NACA 0012 airfoil section. NASA Technical Memorandum 4074, Langley Research Center, Hampton, Virginia, 1988, 95 p.
2. Available at: https://turbmodels.larc.nasa.gov/naca0012_val.html (accessed 19.04.2024).
3. Thomas, J.L. and Salas, M.D. Far-field boundary conditions for transonic lifting solutions to the Euler equations. AIAA Journal, 1986, 24 (7), 1074–1080. DOI: 10.2514/3.9394.
4. Volkova, A.O. and Streltsov, E.V. Numerical study of jet perforated boundaries in the flow over the profile NACA-0012. Trudy MFTI, 2019, 11 (3), 116–125. (In Russian).
5. Isaev, S.A. Circular flow around a NACA 0012 profile at Re=40000: paradoxes of modelling in unsteady aerodynamics. Sovremennaya Nauka: Issledovaniya, Idei, Rezultaty, Tekhnologii, 2012, 2 (10), 226–231. (In Russian).
6. Available at: https://turbmodels.larc.nasa.gov/index.html (accessed at: 19.02.2024).
7. Available at: https://help.sim-flow.com/tutorials/airfoil-naca-0012
8. Salmanov, E.G. Research the lift of the double infinite-span wing with a NACA-0012 profile depending on the chord and the vertical interval using Ansys CFX. Sovremennye Nauchnye Issledovaniya i Innovatsii, 2016, 8. (In Russian). Available at: https://web.snauka.ru/issues/2016/08/71052 (accessed 19.04.2024).
9. Chernova, A.A. Validation of rans turbulence models for the conjugate heat exchange problem. Russian Journal of Nonlinear Dynamics, 2022, 18 (1), 61–82. DOI: 10.20537/nd220105.
10. Menter, F., Kuntz, M., and Langtry, R. Ten years of industrial experience with the SST turbulence model. In: Proceedings of the Fourth International Symposium on Turbulence, Heat and Mass Transfer, 2003, 4, 625–632.
11. Galperin, V.G., Gorsky, I.P., Kovalev, A.P., and Khristianovich, S.A. The physical basis of transonic aerodynamics. Uchenye Zapiski TsAGI, 1974, 5 (5). (In Russian).

Article reference