Numerical Analysis of Wing Vortex Interaction in Tandem Wing Configuration
Disciplines
Aerospace Engineering | Mechanical Engineering
Abstract (300 words maximum)
This research investigates the aerodynamic performance of a tandem wing configuration, specifically analyzing angle of attack variations, as well as stagger distance and gap adjustments. The central research question focuses on optimizing the relative placement of the front (NACA 2412) and rear (NACA 0012) airfoils to maximize aerodynamic efficiency. Understanding these interactions is crucial for improving the design of unmanned aerial vehicles (UAVs) and other experimental aerospace applications where tandem wing configurations offer potential advantages over conventional single-wing designs.
For results, Computational Fluid Dynamics (CFD) simulations are conducted using ANSYS Fluent. The k-ω SST turbulence model is used to efficiently capture flow separation and wake interactions. Multiple rear airfoil positions and angles of attack are tested to determine their impact on aerodynamic efficiency, specifically the lift-to-drag ratio (L/D) and wake formation.
Results so far indicate that a moderate stagger distance (1.0–2.0x the airfoil chord) and a slightly higher rear wing AoA optimize the lift-to-drag ratio (L/D). Analysis of wake interactions revealed that improper rear wing positioning leads to increased flow separation and turbulence, reducing overall efficiency. With optimal positioning, the rear wing may partially recover energy from the front wing's downwash, improving lift generation without excessive drag penalties.
Academic department under which the project should be listed
SPCEET - Mechanical Engineering
Primary Investigator (PI) Name
Gaurav Sharma
Numerical Analysis of Wing Vortex Interaction in Tandem Wing Configuration
This research investigates the aerodynamic performance of a tandem wing configuration, specifically analyzing angle of attack variations, as well as stagger distance and gap adjustments. The central research question focuses on optimizing the relative placement of the front (NACA 2412) and rear (NACA 0012) airfoils to maximize aerodynamic efficiency. Understanding these interactions is crucial for improving the design of unmanned aerial vehicles (UAVs) and other experimental aerospace applications where tandem wing configurations offer potential advantages over conventional single-wing designs.
For results, Computational Fluid Dynamics (CFD) simulations are conducted using ANSYS Fluent. The k-ω SST turbulence model is used to efficiently capture flow separation and wake interactions. Multiple rear airfoil positions and angles of attack are tested to determine their impact on aerodynamic efficiency, specifically the lift-to-drag ratio (L/D) and wake formation.
Results so far indicate that a moderate stagger distance (1.0–2.0x the airfoil chord) and a slightly higher rear wing AoA optimize the lift-to-drag ratio (L/D). Analysis of wake interactions revealed that improper rear wing positioning leads to increased flow separation and turbulence, reducing overall efficiency. With optimal positioning, the rear wing may partially recover energy from the front wing's downwash, improving lift generation without excessive drag penalties.