Effects of Wing Spacing on the Aerodynamic Performance of Tandem Wing Configurations
Disciplines
Aerodynamics and Fluid Mechanics | Aerospace Engineering
Abstract (300 words maximum)
Tandem wing configurations, which employ two lifting surfaces arranged in series along the flow direction, have gained attention for their potential to improve aerodynamic efficiency and stability in low-speed flight regimes. This study investigates the influence of the spacing distance between two slightly modified SD7003 airfoils on the aerodynamic performance of a tandem wing arrangement. Two-dimensional steady-state simulations were conducted using a pressure-based solver in ANSYS Fluent under incompressible flow conditions at an inlet velocity of 11 m/s. The computational setup employed velocity-inlet and pressure-outlet boundary conditions, with symmetry applied to the top and bottom boundaries and no-slip conditions at the airfoil surfaces. The k–ω SST turbulence model was used to capture near-wall effects and flow separation accurately. Key aerodynamic parameters, including lift, drag, and lift-to-drag ratio, were analyzed across multiple spacing distances to determine an optimal configuration. The results aim to provide insights into the aerodynamic interactions between the front and rear airfoils, contributing to the design of efficient tandem-wing UAVs and micro air vehicles.
Use of AI Disclaimer
yes
Academic department under which the project should be listed
SPCEET – Mechanical Engineering
Primary Investigator (PI) Name
Gaurav Sharma
Effects of Wing Spacing on the Aerodynamic Performance of Tandem Wing Configurations
Tandem wing configurations, which employ two lifting surfaces arranged in series along the flow direction, have gained attention for their potential to improve aerodynamic efficiency and stability in low-speed flight regimes. This study investigates the influence of the spacing distance between two slightly modified SD7003 airfoils on the aerodynamic performance of a tandem wing arrangement. Two-dimensional steady-state simulations were conducted using a pressure-based solver in ANSYS Fluent under incompressible flow conditions at an inlet velocity of 11 m/s. The computational setup employed velocity-inlet and pressure-outlet boundary conditions, with symmetry applied to the top and bottom boundaries and no-slip conditions at the airfoil surfaces. The k–ω SST turbulence model was used to capture near-wall effects and flow separation accurately. Key aerodynamic parameters, including lift, drag, and lift-to-drag ratio, were analyzed across multiple spacing distances to determine an optimal configuration. The results aim to provide insights into the aerodynamic interactions between the front and rear airfoils, contributing to the design of efficient tandem-wing UAVs and micro air vehicles.