Abstract: Present the two-layer model of thin shock layer-for approximate calculation of the inviscid flow over 3-d sharp bodies.A position of shock wave is defined numerically in this method.The method allows to define approximate values of gas-dynamic loads for calculation of aerodynamic characteristics on different body configurations.The using of this method practically removes restrictions on geometry of a sharp body,which exists for other known methods of hypersonic theory.Together with general aerodynamic characteristics,the method allows to obtain approximate flow fields around integrated schemes of vehicles at design and undesign regimes of the flight,and also it allows to make optimization their aerodynamic forms.