Modification of Horizontal Tail Wing of the 1953 Buhwal Aircraft for Improved Aerodynamic Performance and Stability

摘要

This study is carried out in order to improve the aerodynamic performance and flight stability of the Buhwal aircraft without altering its external shape. The aerodynamics of the Buhwal aircraft were calculated for four different types of horizontal tails: the exiting flat-type, an NACA airfoil, a double wedge airfoil, and an arc shape airfoil. Digital DATCOM was used to shorten the calculation time. By analyzing the lift coefficient, drag coefficient, pitching moment coefficient, and pressure-centric static margin, the wing shape most suitable for aerodynamic characteristics and stability was selected. By doing so, the study was able to improve the Buhwal's aerodynamic performance and static stability without changing the location of the horizontal tail. The NACA airfoil was selected to improve the Buhwal's lift-to-drag ratio, maintain the desired attitude, and ensure greater stability during level flight. A CFD-based analysis was also conducted to calculate the aerodynamics of the Buhwal aircraft with the NACA airfoil attached.