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Numerical study on flow characteristics of supersonic inlet disturbed by backpressure of rotating detonation(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年06期
Page:
85-91
Research Field:
目次
Publishing date:

Info

Title:
Numerical study on flow characteristics of supersonic inlet disturbed by backpressure of rotating detonation
Author(s):
MO Jianwei;  YAN Yu;  YANG Jianwen
(Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
supersonic inlet periodic rotating back pressure flow characteristics
PACS:
V211.3
DOI:
-
Abstract:
In order to study the flow characteristics of the rotating detonation engine inlet under the action of rotating back pressure,a simplified model of the periodic backpressure of the rotating detonation engine was established, and the unsteady numerical simulation method was used to study the flow characteristics of the twin inlet under the action of rotating detonation back pressure.The results show that the iso-pressure surface of the flowfield presents an irregular spiral shape under the action of periodic rotating back pressure with the distorted flow condition,which is different from the flow characteristic in the isolation section of uniform inlet flow.The rotating pressure wave is blocked at the intersection of the two ducts, and the flow of two ducts tends to be steady before the intersection section.The leading edge of the shock train at the end of the inlet is basically the same under periodic rotating back pressure and steady state back pressure, indicating that the performance under the periodic backpressure of the inlet is not different from that under the steady-state condition.

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