Modification of Horizontal Tail Wing of the 1953 Buhwal Aircraft for Improved Aerodynamic Performance and Stability
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 Buhwals aerodynamic performance and static stability without changing the location of the horizontal taiL The NACA airfoil was selected to improve the Buhwals 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.
Buhwal aircraft Aerodynamic performance Stability Horizontal tail wing Digital DATCOM
J.G.Oh S.K.Jung Y.R.Yang T.H.Cho R.S.Myong K.R.Park
Department of Mechanical and Aerospace Engineering Gyeongsang National University Jinju,Gyeongnam 66 Department of Mechanical and Aerospace Engineering Gyeongsang National University Jinju, Gyeongnam 6
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
79-81
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）