Ensuring the safety of human spaceflight programs, particularly during the critical re-entry phase where the combination of high speeds and compression can result in temperatures well above 2000 ℃, is of paramount importance. In this context, the reduction of aerodynamic heating and the development of efficient thermal protection systems are crucial. In this study, active thermal protection system is envisaged, i.e., counterflow. The studies conducted by Hayashi, including both wind tunnel experiments (Hayashi and Aso in Effect of pressure ratio on aerodynamic heating reduction due to opposing jet. In: 36th AIAA thermophysics conference, p 4041, 2003, [1]) and numerical simulations (Hayashi et al. in Numerical study of thermal protection system by opposing jet. In: 43rd AIAA aerospace sciences meeting and exhibit, p 188, 2005, [2]), played a crucial role in uncovering the fundamental aspects of an opposing jet. In this project, the findings from Hayashi’s experiments were utilized to establish a basis for comparison and further analysis. The primary focus is on implementing an opposing jet within the crew module structure. A comprehensive numerical analysis is performed on the crew module, similar to that conducted on the blunt body, with a specific emphasis on studying the reduction in wall heat flux achieved through the implementation of the opposing jet.