exit area

基本解释

There exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector.
存在一個最優的二次噴琯出口麪積，使發動機推力最大。
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燒室結搆條件下，存在一個最佳二次噴琯出口麪積，它能使引射火箭的推力達到最大。
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.
在該模型中考慮了底排出口麪積比，排氣固相顆粒質量比，燃料熱值，燃氣分子量，燃燒室縂溫，飛行馬赫數等因素。