This study numerically investigates transonic shock wave characteristics over supercritical airfoils using the OpenFOAM-based open-source solver TSLAeroFoam. The numerical setup is validated through comparison with benchmark transonic experimental results. A parametric study is conducted by varying the Mach number from 0.72 to 0.78 and the angle of attack from 3° to 7° to evaluate their effects on shock position, strength, shock–boundary layer interaction, and associated aerodynamic coefficients including lift, drag, and moment. Results indicate that increasing the angle of attack causes shock to move upstream toward the leading edge. Increasing the Mach number leads to a reduction in pressure on the lower surface and a corresponding decrease in lift coefficient. At a fixed angle of 3°, the lift coefficient dropped from nearly 0.71 to 0.60 as Mach number increased from 0.72 to 0.78. Additionally, the lift-to-drag ratio decreased significantly with both Mach number and angle of attack, dropping from approximately 37 to 16 at 3°, and from 12 to 8 at 7° for Mach numbers 0.72 and 0.78, respectively. The findings collectively demonstrate that both Mach number and angle of attack influence shock wave behavior and aerodynamic performance in transonic flows, with stronger effects observed at higher values of both parameters.
| Primary Language | English |
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| Subjects | Aerodynamics (Excl. Hypersonic Aerodynamics), Computational Methods in Fluid Flow, Heat and Mass Transfer (Incl. Computational Fluid Dynamics), Turbulent Flows, Renewable Energy Resources , Heat Transfer in Automotive |
| Journal Section | Research Article |
| Authors | |
| Publication Date | December 1, 2025 |
| Submission Date | July 16, 2025 |
| Acceptance Date | August 12, 2025 |
| Published in Issue | Year 2025 Volume: 13 Issue: 4 |