The Viscous Correction Research During the Aerodynamics Calculation Via Euler Equation

During the aerodynamics calculation via Euler equation, the estimation of drag entirely by surface pressure integration is the normal pressure drag. The inviscid Euler drag solution is separated into an induced drag component and a wave drag component. The boundary layer correction is needed for viscid drag. The Cohen-Reshotko's method is used to calculate the steady twodimensional laminar boundary layer. The Granville's method is used to compute the boundary layer transition and the Green's is used to calculate the turbulent boundary layer. The lift and drag coefficient via viscous correction is closer to the result of the wind tunnel test.