Aerodynamic Analysis of Inflatable Wings with Variable Baffle Configurations

This study investigates the aerodynamic performance of inflatable wings (IWs) with variable baffle configurations using computational fluid dynamics (CFD) simulations. By transforming a baseline NACA 4318 airfoil into bumpy profiles through a validated baffle-based bumpy airfoil generation algorithm, the research systematically evaluates the effect of internal and external bumps for lift, drag, and overall aerodynamic efficiency across Reynolds number (Re = 2e5) and (6e5). Externally baffled configurations, particularly those with 19 compartments (C19), exhibited enhanced lift and delayed flow separation through vortex-induced reattachment, yielding improved efficiency at low-to-moderate Re. Conversely, internally baffled airfoils underperformed due to insufficient surface perturbations to trigger favorable flow structures. The analysis reveals a trade-off between vortex-driven lift generation and pressure drag penalties at higher angles of attack, with external baffles offering aerodynamic advantages in subsonic UAV flight regimes. These insights inform the selection of a bumpy airfoil design for deployable wing applications requiring compact storage and reliable aerodynamic performance.