Abstract IN this paper we describe a finite-difference method of solving the equations of a laminar boundary layer, based on a difference representation of equations written as integrals. The method is used to calculate the characteristics of a laminar boundary layer in a hypersonic nozzle. Here account is taken of the actual properties of air at high temperatures ( T eo = 1000 ÷ 5000° K, P eo = (100 ÷ 200) · 1.01325 · 10 5 H/M 2 ) . The current in the external How and the boundary layer are assumed to be in equilibrium. The results of calculations of similar currents by the method of generalized integral relations of A.A. Dorodnitsyn [1, 2] are given for comparison.