A detailed laminar flow field within the normal shock wave considering variable specific heats, viscosity and Prandtl numbers

The gas flow field within an 1D normal shock wave at variable specific heats, viscosity and Prandtl numbers with temperature is considered. At Pr = 0.75 and constant specific heats and viscosity, the already known analytical solution in a somehow different form is found. At some distance from the wave, the flow is isoenergetical (constant total enthalpy). In order to see if the isoenergetical character of flow within the shock wave is maintained, a method to correct the solution for variable Prandtl number is developed. The obtained solution is close to an analytical one and proves that the deviation from the constant enthalpy hypothesis is less than 0.5%. An interesting thing pointed out is the coexistence of the supersonic and subsonic regimes within the shock wave. Examples of application for air at two Mach numbers are given.