NACA-0006 Aerodynamic Characterization of Airfoil High-Speed Flow Field

With the continuous expansion of China's civil aviation capacity, higher requirements have been put forward for the aerodynamic shape of aircraft wings in order to achieve higher economic efficiency and enhance the efficiency of aircraft transportation. When the Mach number of the airplane is increasing, the surface of the wing will exist supersonic region, subsonic region and transonic region, and present different aerodynamic properties. In this paper, the aerodynamic performance of NACA-0006 typical airfoil in supersonic region and subsonic region is analyzed in depth, and simulation experiments are carried out to obtain the aerodynamic performance parameters of this airfoil by GAMBIT and FLUENT software; the aerodynamic properties of NACA-0006 airfoil such as the coefficient of lift, the coefficient of drag, the coefficient of moment, as well as the position of the excitation wave generation on the wing, etc., are analyzed with the change of Mach number. The aerodynamic characteristics of NACA-0006 airfoil are analyzed under different Mach numbers, and the trends of the lift coefficient, drag coefficient, moment coefficient, and the location of surge generation on the airfoil are analyzed, and the critical Mach number of the airfoil is found.