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.
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。
Results show that the maximum stress appears in entrance area of the nozzle and minimum stress in middle area, while the stress of exit area is lower than entrance area and higher than middle area.