exit area

基本解释

There exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector.
存在一个最优的二次喷管出口面积，使发动机推力最大。
There exists an optimal exit area of secondary nozzle to result in a maximum thrust of rocket ejector in the light of the investigated ejector chamber structure.
在文中所研究的引射燃烧室结构条件下，存在一个最佳二次喷管出口面积，它能使引射火箭的推力达到最大。
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。