Parametric study of a corrugated airfoil in a forward flight at ultra-low Reynolds number

Abstract In the current study, mid cross section of dragonfly forewing was simulated at ultra-low Reynolds number. The study aims to understand better contribution corrugations found along wing on aerodynamic performance during a forward flight. Different flapping parameters were employed. FLUENT solver used solve unsteady, two-dimensional, laminar, incompressible Navier–Stokes equations. results revealed that any stroke amplitude less than 1 c m generated no thrust force. had be increased form reversed Kármán vortices responsible for generating highest propulsive efficiency in Strouhal number range 0.2 < St 0.4 with peak 57% = 0.39. Changing phase difference between pitching and plunging motions from advanced synchronized caused lift force drop 91% increase by 15%. On other hand, changing delayed forces 89% 36%, respectively, deteriorate significantly. all performed simulations, airfoil assumed start motion rest initial angle attack. attack generates very high fair loss both efficiency. decomposition into its elementary are non-linear superposition pure forces. This can attributed interaction unsteady these decomposed motions.