Low-reynolds-number flowfield of wing with control surface in propeller slipstream

Tsubasa Ikami; Koji Fujita; Hiroki Nagai

doi:10.2514/1.C035880

Low-reynolds-number flowfield of wing with control surface in propeller slipstream

Tsubasa Ikami, Koji Fujita, Hiroki Nagai

IFS - Creative Flow Research Division

Tohoku University

Research output: Contribution to journal › Article › peer-review

3 Citations (Scopus)

Abstract

An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 × 10⁴ . The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.

Original language	English
Pages (from-to)	228-235
Number of pages	8
Journal	Journal of Aircraft
Volume	58
Issue number	2
DOIs	https://doi.org/10.2514/1.C035880
Publication status	Published - 2021

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abstract = "An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 × 104 . The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.",

author = "Tsubasa Ikami and Koji Fujita and Hiroki Nagai",

note = "Funding Information: This work was supported by Japan Society for the Promotion of Science (JSPS) KAKENHI (grant number: JP17H03474). The authors would like to thank Y. Konishi, H. Okuizumi, and K. Takahashi for supporting the wind-tunnel test. Publisher Copyright: {\textcopyright} AIAA International. All rights reserved.",

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doi = "10.2514/1.C035880",

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AU - Ikami, Tsubasa

AU - Fujita, Koji

AU - Nagai, Hiroki

N1 - Funding Information: This work was supported by Japan Society for the Promotion of Science (JSPS) KAKENHI (grant number: JP17H03474). The authors would like to thank Y. Konishi, H. Okuizumi, and K. Takahashi for supporting the wind-tunnel test. Publisher Copyright: © AIAA International. All rights reserved.

PY - 2021

Y1 - 2021

N2 - An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 × 104 . The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.

AB - An experimental study is conducted on a NACA 0012 airfoil with a control surface to investigate the influence of a propeller slipstream under a low-Reynolds-number condition. To investigate the influence of the propeller slipstream on a wing surface, the flowfield on the wing surface is visualized using a temperature-sensitive paint when the chord-based Reynolds number is equal to 3.0 × 104 . The control surface performance improves in the installed-propeller condition because the propeller slipstream suppresses the laminar separation bubble. Finally, we suggest that the propeller should be installed ahead of the control surface to benefit from the effect of the propeller slipstream under the low-Reynolds-number flight condition.

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Low-reynolds-number flowfield of wing with control surface in propeller slipstream

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