@article{article_1743613, title={NUMERICAL INVESTIGATION OF TRANSONIC SHOCK WAVE CHARACTERISTICS ON SUPERCRITICAL AIRFOILS UNDER VARIOUS FLOW CONDITIONS}, journal={Konya Journal of Engineering Sciences}, volume={13}, pages={1252–1263}, year={2025}, DOI={10.36306/konjes.1743613}, author={Kaya, Mehmet Numan}, keywords={CFD, OpenFOAM, RAE2822, Shock, Transonic, Wave}, abstract={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.}, number={4}, publisher={Konya Technical University}