This study examines the aerodynamic benefits of implementing a sinusoidal leading edge on a lambda-shaped, subsonic flying wing with a 56-degree sweep angle and -3-degree twist. Numerical simulations, validated by experimental data over angles of attack from -5° to 20°, focused on optimizing lift, drag, and vortex formation. Results show that the sinusoidal leading edge improves the lift-to-drag ratio by approximately 20% within the 5° to 15° range, enhancing range and reducing fuel consumption. Unlike conventional dual-vortex structures, vortices form at each crest along the sinusoidal edge, potentially delaying flow separation at higher angles of attack by adding turbulent energy and promoting lateral reattachment.

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