Aerodynamic Optimization of Double-Wedge Airfoils with Curved Recesses for High Subsonic and Supersonic Flows

Abstract

The aerodynamic performance of airfoils operating at high subsonic and supersonic speeds is often limited by adverse pressure gradients, boundary layer separation and shock wave formation, leading to increase in drag and reduce the efficiency. This study proposes a modified double-wedge airfoil featuring symmetric curved recesses positioned between the mid-chord region to enhance flow characteristics while preserving geometric simplicity. The conventional sharp edges are replaced with 5 mm and 10 mm deep recesses that generate localized low-pressure zones, thereby mitigating shock intensity and promoting improved pressure recovery. Computational Fluid Dynamics (CFD) analyses are conducted at Mach numbers 0.8, 1.5, 2.0, and 2.5 to evaluate aerodynamic behavior with respect to lift and drag across both high subsonic and supersonic regimes. The influence of varying angles of attack is examined to assess drag reduction, shock structure and boundary layer development. The findings indicate delayed flow separation, improved lift-to-drag ratios and reduced wave drag, especially at higher Mach numbers. Comparative assessments between simulation outcomes and preliminary experimental data validate the proposed design approach. Overall, this work presents a practical modification strategy for enhancing aerodynamic efficiency in advanced airfoil configurations.