Detailed flow field around a leading-edge slat at low Reynolds numbers

Autor:	Makiya, Sanehiro, Inasawa, Ayumu, Asai, Masahito
Jazyk:	angličtina
Rok vydání:	2008
Předmět:	flow distribution 流れの分布 低レイノルズ数 空力騒音 音圧 low Reynolds number high-lift device power spectrum 翼型 層流域後流 Physics::Fluid Dynamics 前縁スラット 渦 aerodynamic characteristic vortex aerodynamic noise leading edge slat パワースペクトル 高揚力装置 sound pressure flow visualization 空力特性 laminar wake airfoil 流れの可視化
Zdroj:	宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集 第40回 = JAXA Special Publication: Proceedings of the 40th JAXA Workshop on Investigation and Control of Boundary-Layer Transition. :27-30
ISSN:	1349-113X
Popis:	Flows around a leading-edge slat are investigated experimentally at Reynolds numbers Re less than or equal to 5.2 x 10(exp 5). When the slat operates to suppress the leading-edge stall, a periodic vortex shedding occurs due to the instability of laminar wake of the slat at Reynolds numbers less than 2.1 x 10(exp 5). The Reynolds number variation of the shedding frequency is not unlike that of the circular-cylinder wake at low Reynolds numbers. For Re greater than or equal to 2.3 x 10(exp 5), prominent spectral peaks appear both in the velocity fluctuations and sound-pressure and the frequency of such distinguished noise is found to be proportional to U(sub infinity)(exp 0.84) as reported in the experiment on the sound generation in a single-element airfoil at small angles of attack, suggesting a possibility of feedback loop between the shear layer instability immediately upstream the slat trailing-edge and the generated sound. 資料番号: AA0063908009 レポート番号: JAXA-SP-07-026E
Databáze:	OpenAIRE
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