The basis of stable model is MESH equation, or mass, vapor-liquid, component addition, and enthalpy equilibrium equations.
稳态模型建立的基础是MESH方程，即物料平衡方程、相平衡方程、组分加和方程和焓平衡方程。
The algebraic expressions of enthalpy flux and mass flow rate in regenerator as well as the phase difference between pressure and mass flow rate at pulse tube cold end are presented.
得到了通过回热器的焓流、质量流量及脉管冷端压力和流量相位差的代数计算公式。
In the model the exit area ratio, solid particle mass ratio, fuel enthalpy of combustion, jet gas molecular weight, chamber stagnation temperature, flight Math number etc. have been considered.
在该模型中考虑了底排出口面积比，排气固相颗粒质量比，燃料热值，燃气分子量，燃烧室总温，飞行马赫数等因素。
In the model the exit area ratio, solid particle mass ratio, fuel enthalpy of combustion, jet gas molecular weight, chamber stagnation temperature, flight Math number etc. have been considered.
在该模型中考虑了底排出口面积比，排气固相颗粒质量比，燃料热值，燃气分子量，燃烧室总温，飞行马赫数等因素。
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