Transonic state in compressible flows depends on the geometry, Mach number and the incidence. The supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. Transonic flow occurs a transition state from subsonic to supersonic local flow in the same flowfield under Mach number from M=0.8 to 1.2. As the Mach number increases, shock waves appear in the flowfield. The transonic aerodynamics characteristics on Onrea M6 Wing is studied by using ANSYS CFX in transonic region. For the results, As the speed increase the shock waves get stronger. The shock waves lead to a rapid increase in drag.