Abstract: In this paper the results of calculations of the coefficients of skin friction and heat transfer(Stanton number) on the surface of hypersonic flight vehicle are presented.Two methods,namely"The plane sections method" i.e. 2D boundary layer approximation and "The engineering method", are used for calculation of viscous effects at hypersonic flow around the flight vehicle. Calculation results of both methods are presented and compared in detail. It can be seen from this article that the two methods have demonstrated the working capacity for calculation of frictional force and thermal load on surface of a hypersonic winged flight vehicle, which moves in dense atmospheric layers on a trajactory with stationary values of velocity head. They can successfully be applied to parametric calculations for flow around bodies of complex form.