Numerical Analysis of Wing Vortex Interaction in Tandem Wing Configuration
Disciplines
Aerodynamics and Fluid Mechanics | Aeronautical Vehicles
Abstract (300 words maximum)
Unmanned aerial vehicles (UAVs) are increasingly shaping the future of aviation, with many nations prioritizing their development. Among various configurations, tandem-wing designs have been widely explored for UAV applications due to their advantages in stability, payload capacity, and aerodynamic efficiency. Similar to conventional wings, each wing in a tandem configuration generates leading-edge vortices, which, in turn, influence the vortex formation on the trailing wing. This interaction can enhance aerodynamic efficiency but may also contribute to increased drag.
This study investigates the aerodynamic effects of vortex interactions in tandem-wing configurations through numerical simulations. The analysis focuses on the NACA 2412 airfoil with a chord length of C = 1 meter, examining variations in horizontal (x) and vertical (y) spacing between the leading and trailing wings, angles of attack (α), and Mach numbers (M). The parametric ranges include x = [1C, 3C], y = [0.5C, 2C], α = [0°, 15°], and M = [0.4, 0.6]. Given that Mach numbers exceed 0.3, all simulations account for compressibility effects.
To accurately capture vortex propagation and unsteady shedding dynamics, the study employs Unsteady Reynolds-averaged Navier–Stokes (URANS) equations, using the SST k-ω turbulence model. The findings contribute to a deeper understanding of vortex behavior in tandem-wing configurations, offering insights for optimizing UAV aerodynamic performance.
Academic department under which the project should be listed
SPCEET - Mechanical Engineering
Primary Investigator (PI) Name
Dr. Gaurav Sharma
Numerical Analysis of Wing Vortex Interaction in Tandem Wing Configuration
Unmanned aerial vehicles (UAVs) are increasingly shaping the future of aviation, with many nations prioritizing their development. Among various configurations, tandem-wing designs have been widely explored for UAV applications due to their advantages in stability, payload capacity, and aerodynamic efficiency. Similar to conventional wings, each wing in a tandem configuration generates leading-edge vortices, which, in turn, influence the vortex formation on the trailing wing. This interaction can enhance aerodynamic efficiency but may also contribute to increased drag.
This study investigates the aerodynamic effects of vortex interactions in tandem-wing configurations through numerical simulations. The analysis focuses on the NACA 2412 airfoil with a chord length of C = 1 meter, examining variations in horizontal (x) and vertical (y) spacing between the leading and trailing wings, angles of attack (α), and Mach numbers (M). The parametric ranges include x = [1C, 3C], y = [0.5C, 2C], α = [0°, 15°], and M = [0.4, 0.6]. Given that Mach numbers exceed 0.3, all simulations account for compressibility effects.
To accurately capture vortex propagation and unsteady shedding dynamics, the study employs Unsteady Reynolds-averaged Navier–Stokes (URANS) equations, using the SST k-ω turbulence model. The findings contribute to a deeper understanding of vortex behavior in tandem-wing configurations, offering insights for optimizing UAV aerodynamic performance.