Static Aeroelastic Analysis of a Supersonic Flight Vehicle with a Ramjet Engine

Kwak, Jun-young; Hong, Wooram; Shin, Su-Jung; Lee, Il; Yim, JinWoo; Kim, Chongam

doi:10.2514/6.2010-2636

Cited by 2 publications

(1 citation statement)

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“…This sequence of unsteady processes is referred to as inlet buzz, which provokes a number of efficiency problems regarding the ramjet. The inlet buzz can cause more serious problems such as thrust loss, non-starting of the engine, and even structural damages to the aircraft [1,2]. In order to define the buzz occurrence mechanism and to control it, many precedent researches have been conducted in experimental and/or numerical analysis fields.…”

Section: Introductionmentioning

confidence: 99%

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

Namkoung¹,

Hong²,

Kim³

et al. 2012

International Journal of Aeronautical and Space Sciences

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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.Key words: supersonic inlet buzz, effect of angle of attack, asymmetric shock structure, distortion This is an Open Access article distributed under the terms of the Creative Commons Attribution Non-Commercial License (http://creativecommons.org/licenses/bync/3.0/) which permits unrestricted non-commercial use, distribution, and reproduction in any medium, provided the original work is properly cited.

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Section: Introductionmentioning

confidence: 99%