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CFD Analysis of F-16 Wing Airfoil Aerodynamics in Supersonic Flow

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The Science and Development of Transport—ZIRP 2021

Abstract

Aerodynamic characteristics of the NACA 64A-204 airfoil are evaluated by numerical analysis of the turbulent flow at compressible and high Mach number using computational fluid dynamics (CFD). The simulations were done using the Ansys Fluent 2021R Academic Version. The results are obtained with Reynolds averaged Navier–Stokes (RANS), and for resolving of the flow turbulence, the k-ω SST turbulence model was selected. The paper shows how a simple simulation-based analysis predicts better aerodynamical characteristics for a wing with changing geometry. It is shown how the maximum ratio of CL/CD for subsonic configuration is 6.9, whereas for supersonic configuration under equal conditions, the max value for CL/CD is 7.1, which is around 2.75% increase. Also, for supersonic flight regime, the supersonic airfoil configuration provides over 10% higher value for CL/CD ratio at 1° angle of attack based on the CFD results. This paper also promotes the wing morphing technologies due to increases in aerodynamical characteristics when the geometry changes. Changing wing geometry could lead to less fuel consumption and less noise creation above urban places with airports inside the city area. It is expected that wing changing geometry will be used not only for military but also for civil supersonic aircraft.

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Correspondence to Karolina Krajček Nikolić .

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Matak, L., Nikolić, K.K. (2022). CFD Analysis of F-16 Wing Airfoil Aerodynamics in Supersonic Flow. In: Petrović, M., Novačko, L., Božić, D., Rožić, T. (eds) The Science and Development of Transport—ZIRP 2021. Springer, Cham. https://doi.org/10.1007/978-3-030-97528-9_13

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