摘要
为了计算高马赫数条件下气体动力学参数,引入无量纲的温度平均比热系数m和对数温度平均比热系数n,从气体动力学和热力学基本概念出发,推导建立了能够反映“变比热效应”的广义气体动力学函数和理论动压表达式。广义气体动力学函数在马赫数<3条件下的简化形式与传统气体动力学函数一致,在马赫数>3条件下能够有效修正“变比热效应”所导致的传统气体动力学函数计算偏差,通过无量纲系数m和n可以便捷得到总静参数的关系式。
In order to calculate the aerodynamic parameters at high Mach number,the dimensionless tem⁃perature average specific heat coefficient m and logarithmic temperature average specific heat coefficient n are in⁃troduced.In view of the basic concepts of gas dynamics and thermodynamics,the generalized gas dynamics func⁃tion and theoretical dynamic pressure expression which can reflect the"variable specific heat effect"are deduced.The simplified form of generalized gas dynamic function is consistent with that of traditional gas dynamic function when Mach number is less than 3.The calculation deviation of traditional gas dynamic function caused by"vari⁃able specific heat effect"can be effectively corrected when Mach number is greater than 3.The total static param⁃eter relationship can be easily obtained by dimensionless number m and n.
作者
刘小勇
贾云涛
张波
郭金鑫
LIU Xiao-yong;JIA Yun-tao;ZHANG Bo;GUO Jin-xin(Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2021年第8期1770-1775,共6页
Journal of Propulsion Technology
基金
高超声速冲压发动机技术重点实验室基金(6142703180213)。
关键词
变比热
气体动力学
基本函数
理论动压
总参数
静参数
Variable specific heat
Gas dynamics
Basic functions
Theoretical dynamic pressure
To⁃tal parameters
Static parameter
