NUMERICAL STUDY OF TRANSPIRATION COOLING ON THE NOSECONE AND FOREBODY OF A REENTRY SHIELD
Very strong aerodynamic heating on the leading edges of spacecraft during reentry necessitates effective cooling of the surface to prevent damage. Traditional cooling methods such as ablation cooling and high temperature ceramics have limits which are unsatisfactory. Transpiration cooling is the most promising active cooling method to provide thermal protection for surfaces exposed to the extreme heat fluxes. Research on transpiration cooling has continued for many years and has been successfully applied in the OMS, the J-2 engines and the SSME. This paper presents numerical simulations of transpiration cooling using air and helium on the nosecone and forebody of a reentry vehicle. The simulations examine the influence of various coolant properties on the cooling efficiency of the transpiration cooling and the flow characteristics. The results show that transpiration on curved surfaces can successfully protect the nosecone, the forebody and the downstream window region. A continuous film covers the window region which provides a better thermal environment and reduces the influence of the aero-optics. The results also show that helium is more effective than air for transpiration cooling.
S. S. Jin P. X. Jiang
Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, Tsinghua University, Beijing, 100084, CHINA
国际会议
首届亚洲计算传热与计算流体国际会议(2007 Asian Symposium on Computational Heat Transfer and Fluid Flow)
西安
英文
2007-10-08（万方平台首次上网日期，不代表论文的发表时间）