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前言当外界压力与喷管口压力不等时,由圆截面拉伐尔喷管喷出之超音速气流结构特殊,但直到目前,对上述气流的结构情况所进行的研究工作做得不多。从事上述问题的研究对喷气技术的发展具有重大意义。近年来,由于喷气技术发展本身的需要,对于喷管口压力高于外界压力的情况,特别感到兴趣。当喷口压力P_(?blx)高于外界压力P_H时,如气流射入静止介质或亚音速均匀流场,则圆轴对称超音速气流的结构与二元平面超音速气流的结构之间的差别甚大;因在圆轴对称超音速气流中的膨胀特性线是弯曲的,相应地使得气流边界也形成一曲面并在气流中出现一系列冲波系;此一现象使上述问题的理论解决大大地复杂化了。
Introduction When the external pressure and the nozzle pressure are not equal, the supersonic airflow emitted by the circular section Laval nozzle has a special structure. However, up to now, the research work on the structure of the airflow has not been done much. Research on the above issues is of great significance to the development of jet technology. In recent years, due to the need of jet technology development itself, it is of particular interest for the nozzle pressure to be higher than the external pressure. When the nozzle pressure P _ (? Blx) is higher than the external pressure P_H, such as the jet into the static medium or subsonic uniform flow field, the structure of the circular axisymmetric supersonic flow and the structure of the binary plane supersonic airflow difference Because of the curved line of expansion in the circularly axisymmetric supersonic flow, correspondingly, the boundary of the flow also forms a surface and a series of wave systems appear in the flow of gas. This phenomenon makes the theory of the above problem greatly solved Complicated.