Document Type : Original Article


1 Space Transportation Research Institute, Iranian Space Research Center

2 Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran


The aim of this study is to evaluate the performance of water-jacket cooling system for thermal protection of an exhaust large dimension diffuser at high heat fluxes in a wide range of coolant pressure. For this purpose, a suitable design algorithm has been developed. Using the present method, the parameters of the water-jacket cooling system are determined so that in addition to satisfying the temperature conditions of the metal body, the total pressure drop has remained in the desired range. In the following, the capability of numerical code to design and performance analysis of the cooling system has been evaluated in coolant pressure of 3 to 50 bar and high heat fluxes up to 3.5 MW/m2. The present studies show that the proper selection of coolant pressure is very important in the design of the cooling system with optimal mass flow rate and minimum coolant dimensions, especially at high heat fluxes, so that increasing the coolant pressure from 3 to 10 bar, in addition to significantly reducing the dimensions of the cooling system, reduces the mass flow rate by 75%.