International Journal of Science, Engineering and TechnologyAuthors: Harini R, Sibinesh R V, Jefy Stanly S
Abstract: This study presents a Computational Fluid Dynamics (CFD) investigation into the aerodynamic performance of modified supersonic airfoils, focusing on two novel configurations: a Modified double wedge and a Wedge–convex airfoil. Traditional supersonic airfoils such as the double wedge and biconvex perform effectively at high Mach numbers but often experience increased drag and reduced efficiency at moderate angles of attack. To address these issues, geometric modifications were introduced to improve shock control and pressure distribution. The aerodynamic performance of the modified airfoils was assessed using steady, compressible, two-dimensional CFD simulations. Simulations were conducted across Mach numbers ranging from 1.5 to 4.0 and angles of attack(AOA) of 0°, 2°, 4°, 6°, 10°, and 15°.Key aerodynamic parameters including lift coefficient (CL), drag coefficient (CD), moment coefficient (CM), and lift-to-drag ratio (CL/CD) were evaluated to understand the performance across various flow conditions. Results indicate that the wedge–convex airfoil outperforms the traditional biconvex airfoil, particularly in terms of CL/CD and stability. Among the tested geometries, the wedge–convex airfoil consistently exhibited superior performance, suggesting strong potential for applications in supersonic aircraft wings and missile nose designs.
