TY - JOUR
TI - Study of linear ablative rate of D6AC steel wing used on supersonic missile
AU - Zhao Fei
AU - Su Lanhai
AU - Zhu Rong
AU - Li Zhihui
JN - Thermal Science
PY - 2019
VL - 23
IS - 6
SP - 4107
EP - 4116
PT - Article
AB - 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.