Investigation examines aerodynamic performance and vortex structures of a NACA 2412-based non-slender delta wing, revealing key flow dynamics and implications for design.
Key Points
The aim is to investigate the aerodynamic performance and vortex structures of a NACA 2412-based non-slender delta wing.
Aerodynamic forces including lift and drag coefficients were measured.
Flow structures analyzed using titanium-dioxide-based surface oil visualization and tuft-grid technique.
Vortex cores were evaluated at various chord distances (1C, 2C, and 3C) from the trailing edge.
Maximum lift coefficient recorded at 0.9256 with a 21° angle of attack.
Maximum lift-to-drag ratio reached 5.2553 at 9°.
Vortex cores shifted downward and expanded downstream, contrasting stall characteristics with standard fixed-chord NACA 2412 wings.