Investigation on Flow over Conventional and Supercritical Airfoils at Transonic Regimes

Authors- Mysa Koushik

Abstract- Flow over conventional and supercritical airfoils in the transonic regime is investigated and compared in this study. This study focuses on two-dimensional flow conditions with Mach numbers of 0.8 and 0.9 at Angles of attack (α)00 and 50. Flow over NACA4415 and SC(2)-0410 as examined using the Ansys software by CFD analysis. The computational results indicate that a supercritical airfoil has higher efficiency and performance and delays the formation of shock waves compared with conventional airfoils in the transonic regime. The Mach number and angle of attack affect the generation of shock waves on both airfoil surfaces. SC(2)-0410 and NACA-4415 were compared by considering factors like lift co-efficient CL, drag coefficient C¬D, lift to drag ratio(L/D), and position of formation of the shock wave on the airfoil surface. The behavior of the airfoils in the transonic flow regime was further analysed.

DOI: /10.61463/ijset.vol.12.issue3.182