A new calculation method was proposed for the typical structure of the platelet transpiration flux in the rocketthrustchamber based on the test data of another chamber.
针对典型的层板发汗冷却结构，提出了利用一个推力室的实验数据来计算另一推力室所需发汗流强的方法。
2
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。
3
Heat transfer possibly results in the thermal wrinkling of transpiration cooling platelet of the liquid rocket engine (LRE) 's thrustchamber.