Supersonic laminar flow on windward surface of yawed wedges of infinite span in wide range of Reynolds numbers

The problem of a thin (hypersonic) viscous shock layer describing the disturbed gas flow from the wedge surface to the shock wave in a wide range of Reynolds number is discussed. The solution is obtained in terms of the hydrodynamic model for the problem of supersonic and in particular hypersonic flow on jawed wedges for Reynolds numbers ranged from low values corresponding to the onset of continuum flow to high values when the theory of asymptotic thin boundary layer is applicable. The solution is obtained using the model of viscous shock layer equations being universal and effective numerical methods.