JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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titleUnsteady shock wave motions on a thin airfoil at transonic speeds caused by aileron oscillations
Other Title遷音速における薄翼上衝撃波のエルロン振動による非定常挙動について
Author(jpn)玉山 雅人; 中道 二郎
Author(eng)Tamayama, Masato; Nakamichi, Jiro
Author Affiliation(jpn)宇宙航空研究開発機構 総合技術研究本部; 宇宙航空研究開発機構 総合技術研究本部
Author Affiliation(eng)Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics; Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics
Issue Date2004-03-25
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication date2004-03-25
AbstractAileron buzz is one of the most dangerous phenomena encountered in high-speed flight. If the wing is thin, conventional aileron buzz, which is always accompanied by boundary layer separation, will not occur. In this case, shock wave motions are of great importance in the aileron buzz phenomenon. To acquire fundamental knowledge on this type of aileron buzz, the relationship between shock wave movement and aileron hinge moment have been studied with numerical simulations. A forced aileron oscillation was applied to the unsteady Navier-Stokes simulations around a two-dimensional NACA0003 airfoil with 25 percent chord-length aileron at the trailing edge. In this study, the Mach number, airfoil angle of attack and amplitude and reduced frequency of aileron oscillation were varied. The influence of these parameters on the flow characteristics is described, taking into account the shock wave motions on the aileron surface and the aileron hinge moment. It is observed that, if the shock wave exists on the aileron, it oscillates around a position located upstream of the steady shock wave. The position of a shock wave moving on the aileron is greatly influenced by flow viscosity. It is also observed that the shock wave oscillates non-harmonically, even though the aileron oscillates harmonically. This characteristic was studied by simulating the shock wave motion, assuming a one-dimensional flow field. From this simulation, it is observed that the pressure ratio across a shock wave changes non-harmonically and the shock wave moves non-harmonically.
DescriptionJAXA Research and Development Report
Keywordsunsteady aerodynamics; transonic flow; shock wave; thin airfoil; aileron oscillation; boundary layer; CFD; computerized simulation; 非定常流体力学; 遷音速流; 衝撃波; 薄い翼型; エルロン振動; 境界層; CFD; 計算機シミュレーション
Document TypeTechnical Report
JAXA Category研究開発報告
Report NoJAXA-RR-03-017E

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