Abstract: Accurate computational fluid dynamic (CFD) methods with Novier-Stokes equations and rapid engineering methods are currently two major approaches to obtain skin viscous force for hypersonic aircraft. The former is relatively accurate with poor efficiency, and the later is efficient with poor accuracy. How to combine the two methods and develop a new way with enough efficiency and accuracy is always an important aspect for computational aerodynamics. Therefor, a rapid engineering method to predict skin viscous force of hypersonic aircraft more accurately was developed with near-wall flow characteristics derived from invicid Euler equations. The method was based on the classical reference temperature method and constructed with local flow parameters instead of free flow parameters, so that could count the hypersonic flow characteristics more adequately and achieve a more accurate prediction of skin viscous forces in theory. In order to examine the accuracy of the rapid method, the skin viscous forces of a typical hypersonic aircraft with high Lift-to-Drag ratio at hypersonic velocity and high altitude was calculated by a Navier-Stokes equations CFD method and the presented rapid method. The comparison analysis finally showed a relative deviation of 10~20% from the rapid method, which could gave a good satisfaction for engineering applications.