“…Hoffman [2] studied conical nozzles with nonisentropic flow, without considering a variable geometry. Hurst et al [3] developed experiments and calculated numerically heat transfer coefficients along the hot gas nozzle smooth wall for high-speed boundary layer nozzle flows under engine Reynolds number conditions, presenting a comparison between the experimental and numerical results, showing that the simplification of a local average density in the numerical model leads to good results for transonic and low supersonic flows. Zaccaria et al [4] performed experiments to determine the three-dimensional flowfield in the nozzle of a low-speed, single-stage, axial-flow turbine, comparing the measurements to the numerical results of an existing Navier-Stokes code with good agreement, basically seeking a better understanding of the nozzle flowfield.…”