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Effects of Angles of Attack and Throttling Conditions on Supersonic Inlet Buzz
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Cited 5 time in Scopus
- Authors
- Issue Date
- 2012-09
- Citation
- INTERNATIONAL JOURNAL OF AERONAUTICAL & SPACE SCIENCES Vol.13 No.3, pp. 296-305
- Keywords
- 공학 ; supersonic inlet buzz ; effect of angle of attack ; asymmetric shock structure ; distortion
- 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
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