Study of linear ablative rate of D6AC steel wing used on supersonic missile

Abstract

The D6AC steel wing used on supersonic missile is the object in this study. Its service environment was generated and simulated. The ablation experiment of D6AC steel missile wing was carried out under different parameters of flow field. The ablation process of D6AC steel wing was studied and analyzed under the supersonic aerodynamic heating environment. The results show that the ablation process of D6AC steel missile wing could be divided into three stages: aerodynamic heating, oxidation reaction, and shear stripping. The influence factors of the D6AC, steel wing ablation include the total temperature, Mach number, oxygen content, and water content. The higher the total temperature is, the more early the initial ablation time of wing is. The linear ablative rate of the D6AC steel wing is the result of the interaction of the Mach number, oxygen content, and water content. The higher the Mach number is, the larger the oxygen content is, and the larger the linear ablative rate of missile wing is. The influence of water content on the linear ablative rate of D6AC steel wing is the opposite.