The invention provides a method for designing a conformal supersonic convergent-divergent nozzle, and provides a method for designing a conformal supersonic convergent-divergent nozzle considering both design efficiency and working capability based on a characteristic line method of a shortest length theory and by taking full use of irregular residual space of an engine body, so that the relative position of an inlet and a throat of the nozzle can be flexibly adjusted, and the nozzle can be more accurately designed. The design result is effective and credible. According to the method, the characteristic line theory can be applied to the design of the spray pipe with the small length-diameter ratio, the working capacity of the special-shaped spray pipe under the small length-diameter ratio is improved, and the space utilization rate of the aircraft afterbody is increased.
本发明提供了一种随形超声速收扩喷管设计方法,基于最短长度理论的特征线法,考虑充分利用不规则的机体剩余空间,提出了一种兼顾设计效率与工作能力的随形超声速收扩喷管设计方法,可灵活调整喷管入口与喉道的相对位置,设计结果有效可信。本发明的方法使特征线理论得以用于较小长径比的喷管设计中,改善了小长径比下异形喷管的工作能力,提高了飞行器后体的空间利用率。
Design method of conformal supersonic-speed convergent-divergent nozzle
一种随形超声速收扩喷管设计方法
2024-06-21
Patent
Electronic Resource
Chinese
Experimental and Numerical Investigation of a Supersonic Convergent-Divergent Nozzle
Online Contents | 2012
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