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Abstract

Stability, controllability, and maneuverability are critical factors for aircraft with short takeoff and landing distances, such as modern fighter aircraft and unmanned aerial vehicles. Delta wings are commonly employed in these aircraft due to their efficient aerodynamics, enabling high maneuverability, and performance at both low and high speeds. Nonslender wings are used for low-speed performance and agility, while slender wings offer reduced drag and are suited for high-speed operations. In flight, an aircraft encounters different airflow patterns including vortices that circulate from the higher-pressure lower side of the wing to the lower-pressure upper side, contributing to lift generation. However, as the angle of attack increases, the vortices can become unstable and fluctuate, resulting in induced drag. Understanding this phenomenon is crucial for developing highly stable and maneuverable aircraft. This essay focuses on studying vortex breakdown in delta wings with varying sweep angles and at different AOAs. The essay aims to validate experimental and numerical solutions from previous studies on the variation of vortex breakdown in both slender and nonslender delta wings using computational fluid dynamics. By examining vortex breakdown characteristics in different wing configurations, this essay aims to contribute to developing aircraft designs that prioritize stability and maneuverability.

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