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。
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.
本文用严格的变分法导出了最大推力喷管出口控制面方程。
In this paper, employing rigorous variational calculus, equations of control surface at maximum thrust nozzle exit are derived.
声压级在相交激波点附近出现剧烈变化，喷管出口处的激波和排气羽流造成强噪声。
The sound pressure level changes acutely in shock intersection, and shocks outside nozzle and exhaust plume cause strong noise.
应用推荐