An Innovative Thermal Protection System with Opposing Jet through Extended Nozzle and Film Cooling for Reusable Launch Vehicles

摘要

In order to reduce the aerodynamic heating, the method with opposing jet through extended nozzle, which is attached to the top of semi-sphere surface, is experimentally tested in high enthalpy flows at Mach number of 6.6 with high enthalpy mode of 23 MJ/kg. Experimental results show significant reduction of aerodynamic heating has been realized when higher total pressure of opposing jet is applied with moderate length of extended nozzle. Numerical results show good agreements with experiments. Also experimental study of film cooling has been conducted in high enthalpy flow of 20.5 MJ/kg. At the shoulder of semi-circular configuration coolant gas of helium is injected parallel to free stream and surface heat flux distributions on the flat plate is measured. The results show film cooling in high enthalpy flows are quite effective especially in attached flow area. For practical application a combination of both methods will be highly recommended.