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Study of the buzz mechanism of supersonic inlets(PDF)

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

Issue:
2008年01期
Page:
17-22
Research Field:
研究与设计
Publishing date:

Info

Title:
Study of the buzz mechanism of supersonic inlets
Author(s):
Wang Yufeng; Yang Bao’e
Xi'an Aerospace Propulsion Institute，Xi'an 710100，China
Keywords:
inlet; buzz; separate eddy
PACS:
V211.3
DOI:
-
Abstract:
In this paper buzz of a supersonic mixed-compression inlet with conic multi--compression is studied with numerical method．The periodical change of the pressure recovery and mass flow ratio is calculated on the base of the flow field result．The frequency，amplitude and shock wave train of the terminal shock wave oscillation during buzz process were analyzed．The development of the separated eddy on the compression surface works as a critical factor in inlet buzz based on the analysis of inlet flow field and state parameters．

References:

[1]刘兴洲．飞航导弹动力装置(上)[M]．北京：宇航出版社， 1992．
[2]Goldsmith E L Shock Oscillation Ahead of Centrebody brakes at Supersonic Spocd[R]．AIAAl952-2477．
[3]Sterbentz W H．Cfitefiom for Prediction and Control of Ramjet Flow Flow Puhation[R]．NASA TN 1955-3506．
[4]Pong Jeu Lu,Ling Tzong Jain．Numerical Investigation of Inlet Buzz now Flow[J]．Journal of Propulsion and Power,1998, 14(11)：90-100．

Memo

Memo:
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Last Update: 1900-01-01