When the stagnation temperature of a perfect gas
increases, the specific heats and their ratio do not
remain constant and start to vary with the
temperature. The gas remains perfect; its state
equations remain valid, so it can be named as
calorifically imperfect gas. The aim of this
research is to develop the necessary thermodynamic
and geometrical equations and to study the
supersonic flow at high temperature, lower than the
dissociation threshold. The results are found by the
resolution of nonlinear algebraic equations and
integration of complex analytical functions where
the exact calculation is impossible. The dichotomy
method is used to solve the nonlinear equations and
Simpson’s algorithm for the numerical integration
applied. A condensation of the nodes is used. The
functions to be integrated have a high gradient at
the extremity of the interval of integration. The
comparison is made with the calorifically perfect
gas to determine the error. The application is made
for air in a supersonic nozzle.