According to the results, as the Mach number of the free flow increases, the aerodynamic coefficient values decrease.
📌 3 Key Takeaways
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Objective & Hypothesis:In this study, flow field analysis was performed to determine the aerodynamic coefficients for the SC36210 and NACA0018 airfoil profiles in supersonic compressible flow at 2 Mach.
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Key Findings & Data:According to the results, as the Mach number of the free flow increases, the aerodynamic coefficient values decrease.
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Conclusion & Impact:In addition, Elastic flexible airfoil profiles for use in supersonic wings have higher performance advantages compared to SC36210 and NACA0018 series airfoils.
In this study, flow field analysis was performed to determine the aerodynamic coefficients for the SC36210 and NACA0018 airfoil profiles in supersonic compressible flow at 2 Mach. During this analysis, ANSYS Fluent, and geometric modeling was used. Numerical simulation of flow was made by K-ω Transition turbulence model. Change in the attack angle versus the divergence angle of airfoil surface profile was examined for elastic flexible SC series. According to the results, as the Mach number of the free flow increases, the aerodynamic coefficient values decrease. In addition, Elastic flexible airfoil profiles for use in supersonic wings have higher performance advantages compared to SC36210 and NACA0018 series airfoils.
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