高超音速飞行的总温总压计算  

CALCULATIONS ON TOTAL TEMPERATURE AND PRESSURE IN HYPERSONIC AIR FLOW

作　　者：王绍卿[1] 

机构地区：[1]航空航天部31所

出　　处：《推进技术》1990年第6期29-33,22,共6页Journal of Propulsion Technology

摘　　要：本文用化学平衡定熵变成份变比热热力计算法(以下称热力计算法〕计算了Ma=0～7.00、高度H=0～40km的总温、总压随Ma数及高度H的变化规律.计算结果与定成份定比热的气动函数法(下称气动函数法)和修正系数法的计算结果及R-R公司的引用数据进行了比较.给出了总温、总压的相对误差δ_T、δ_P随Ma数及H的变化规律.计算表明,热力计算法与气动函数法相比较,在Ma>3.0之后有显著的差别.Total temperature and total pressure of a gas flow in chemical equilibrium,isentropy with variable composition and specific heat at Mc = 0-7.0 and H= 0-40km are calculated .The results are compared with those calculated with aerodynamic function method,modifying coefficient method and the method issued by R-R company.In this paper,the variations of total temperature and pressure with Ma and H are presented.The results show that if Ma>3.00, the calculation resalts by thermodynamic method arid aerodynamic function method are remarkably different.For example: at Ma = 6.50,the relative , deviation of total temperature δT>14%, and that of total pressure δP>26%.

关 键 词：航天器 高超音速飞行 气动热力学 气动数据 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]