Numerical simulation of film cooling in supersonic flow (A04)

点击翻译按钮获取中文摘要

Film cooling of a rocket nozzle extension is investigated using direct numerical or large-eddy simulations of the two-component-gas turbulent boundary-layer flow. The simulations of cooling-gas injection through a backward-facing-step slit or by slots or holes at the wall are closely coordinated with the shock-tunnel ex-periments at the RWTH Aachen (sub-project A2) employing gaseous H2O as hot gas and N2, CO2, He, Ar as coolant. The work is aimed at concluding in recommendations for the practical application of film cooling in the nozzle extension, and working out numerical-method and modelling specifications for the demonstrator-concept subproject K4, gained by a combined experimental and numerical effort.