CFD Analysis of Supersonic Flow on Aircraft Wing

The revival of sustainable supersonic transport requires wing designs that minimize wave drag while maintaining lift efficiency at cruise conditions. This study conducts a comprehensive parametric CFD analysis of the NACA 66–206 airfoil (6% thickness) in supersonic flow, varying Mach number (M ∞ = 2.0–3.0), angle of attack (α = 0°–8°), and leading-edge sweep (Λ = 0°–60°) at altitudes of 35,000 ft and 45,000 ft. High-fidelity RANS simulations using ANSYS Fluent with the SST k-ω turbulence model capture shock-boundary layer interactions accurately. Results show sweep reduces wave drag by up to 52% at Λ = 60°, with a 25% improvement in lift-to-drag ratio at moderate sweep angles (Λ ≈ 30°–45°). The supersonic similarity parameter K = α √(M∞² – 1) cos Λ collapses force coefficients within 4% scatter for Λ ≤ 45°, but deviations increase at higher sweep due to three-dimensional relief effects and viscous cross-flow. Detailed flow-field analysis reveals non-intuitive shock weakening mechanisms at high sweep, including reduced effective normal Mach number and spanwise pressure relief. These findings extend classical supersonic theory with modern viscous CFD, providing a validated aerodynamic database for preliminary optimization of next-generation supersonic wings.