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Effects of Angles of Attack and Throttling Conditions on Supersonic Inlet Buzz

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Authors
Namkoung, Hyuck-Joon; Hong, Wooram; Kim, Jung-Min; Yi, JunSok; Kim, Chongam
Issue Date
2012-09
Publisher
The Korean Society for Aeronautical & Space Sciences
Citation
INTERNATIONAL JOURNAL OF AERONAUTICAL & SPACE SCIENCES Vol.13 No.3, pp. 296-305
Keywords
공학supersonic inlet buzzeffect of angle of attackasymmetric shock structuredistortion
Abstract
A series of numerical simulations are carried out to analyze a supersonic inlet buzz, which is an unsteady pressure oscillation
phenomenon around a supersonic inlet. A simple but efficient geometry, experimentally adopted by Nagashima, is chosen
for the analysis of unsteady flow physics. Among the two sets of simulations considered in this study, the effects of various
throttling conditions are firstly examined. It is seen that the major physical characteristic of the inlet buzz can be obtained by
inviscid computations only and the computed flow patterns inside and around the inlet are qualitatively consistent with the
experimental observations. The dominant frequency of the inlet buzz increases as throttle area decreases, and the computed
frequency is approximately 60Hz or 15% lower than the experimental data, but interestingly, this gap is constant for all the test
cases and shock structures are similar. Secondly, inviscid calculations are performed to examine the effect regarding angle of
attack. It is found that patterns of pressure oscillation histories and distortion due to asymmetric (or three-dimensional) shock
structures are substantially affected by angle of attack. The dominant frequency of the inlet buzz, however, does not change
noticeably even in regards to a wide range of angle of attacks.
ISSN
2093-274x
2093-2480
Language
English
URI
http://hdl.handle.net/10371/82308
DOI
https://doi.org/10.5139/IJASS.2012.13.3.154
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Journal Papers (저널논문_기계항공공학부)
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