Impact of specific heat ratio on aerodynamic characteristics of Viking in hypersonic entry to Mars

摘要：

　　Martian atmosphere which is quite different from Earth atmosphere brings a new challenge for aerodynamic prediction of Mars entry vehicles.Appropriate specific heat ratio in perfect gas model of Martian atmosphere will help in fast and massive aerodynamic predictions for trajectory design and layout optimization.Three-dimensional Navier-Stokes equations with real gas model and perfect gas model have been solved by a parallel code to validate the models and the numerical methods,to analyze the effect of specific heat ratio,and to test the accuracy and reliability of perfect gas model in aerodynamic prediction.The good agreement between the numerical results,the reference values and the flight data of Viking validates the physical-chemical models and the numerical methods applied in this paper.Specific heat ratio do have considerable influence on aerodynamic force,smaller specific heat ratio produces bigger absolute value of drag and lift force; perfect gas model with effective specific heat ratio derived from density ratio across the shock results in the most close data to real gas model.

关键词： Martian atmosphere Hypersonic entry Viking Aerodynamic characteristic Specific heat ratio

作者: Junming LYU Junhong LI Qi LI Wenbo MIAO Xiaoli CHENG

作者单位: China Academy of Aerospace Aerodynamics, Beijing 100074, China Beijing Institute of Spacecraft System Engineering, Beijing 100094,China

会议类型: 国际会议

会议名称: The 8th International Conference of Computational Fluid Dynamics, (ICCFD8)(第八届国际计算流体力学会议)

会议地点: 成都

会议语种:英文

页码: 1-8

在线出版日期: 2014-07-25（万方平台首次上网日期，不代表论文的发表时间）