This research paper presents a meticulous
investigation that was conducted by the authors for the
effects of variable length V-shaped leading-edge
morphing on drag reduction in NACA 0012 vertical
stabilizers. This study aimed at enhancing the
aerodynamic performance of these critical aircraft
components under transonic conditions. Employing
computational fluid dynamics (CFD) analysis, the
researchers explored the potential of V-shaped leading-
edge morphing in improving the overall aerodynamic
efficiency. Through systematic simulations and rigorous
analysis, the researchers were able to provide valuable
insights into the effects of different leading-edge lengths
and angles of attack on drag coefficients and lift
performance. While the outcomes did not yield a
significant reduction in drag, this research significantly
contributes to the ongoing exploration of innovative
techniques in aerodynamics for mitigating drag penalties
in vertical stabilizers
