Simulations of supercritical nitrogen flow in cooling channels are compared with experimental results provided by EADS-Astrium Ottobrunn. The objective is to extend and validate the DLR-Tau code to compute and predict the heat transfer in cooling channels of liquid rocket engines. To simulate the flow accurately, the roughness of the surface, the thermophysical properties of the supercritical fluid, as well as the conduction in the structure are modeled.
Analysis of the Heat Transfer in Liquid Rocket Engine Cooling Channels
2010
8 Seiten
Conference paper
English