Numerical study of ways to prevent side loads in an over–expanded rocket nozzles during the launch stageстатья
Статья опубликована в высокорейтинговом журнале
Информация о цитировании статьи получена из
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Статья опубликована в журнале из списка Web of Science и/или Scopus
Дата последнего поиска статьи во внешних источниках: 11 ноября 2019 г.
Аннотация:The paper aims to study an issues of ensuring the safe launch of spacecraft. The phenomenon of a turbulent boundary layer separation from the rocket engine nozzle wall intensively studied in the overexpansion mode that is realized at the start–up stage at sea–level. The emergence of the so–called restricted flow separation leads to the side loads on the wall of the nozzle, the shaking the structure and the destruction of the engine. The conditions for the realization of restricted or free shock separation in the thrust–optimized contoured nozzles of rocket engines are studied numerically. A hysteresis was obtained when changing the type of separation at the stages of increasing and decreasing pressure at the nozzle inlet with the same ambient pressure. Two ways of controlling the transition from one type of separation to another one were studied numerically. The numerical simulation of separated flow in a model nozzle with a back cone shaped extension was carried out. The numerical results confirm that in the nozzle with the large back cone the restricted shock separation can arise and this result appears to be in agreement with experiment.