Flow field on wing surface with control surface in propeller slipstream at low reynolds number

Tsubasa Ikami, Kensuke Kanou, Koichi Takahashi, Koji Fujita, Hiroki Nagai

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

An experimental study is conducted on a NACA0012 airfoil with a control surface to investigate an influence of a propeller slipstream under low Reynolds number condition. To investigate the influence of the propeller slipstream on a wing surface, a flow field on the wing surface is visualized using the Temperature-Sensitive Paint at the chord-based Reynolds number of 3.0×104. Control surface performance improves in the propeller installed condition because laminar separation bubble is suppressed by the propeller slipstream. Finally, we suggest the propeller should be installed ahead of the control surface to use the effect of the propeller slipstream under low Reynolds number flight condition.

Original languageEnglish
Title of host publicationAIAA Scitech 2019 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105784
DOIs
Publication statusPublished - 2019 Jan 1
EventAIAA Scitech Forum, 2019 - San Diego, United States
Duration: 2019 Jan 72019 Jan 11

Publication series

NameAIAA Scitech 2019 Forum

Conference

ConferenceAIAA Scitech Forum, 2019
CountryUnited States
CitySan Diego
Period19/1/719/1/11

ASJC Scopus subject areas

  • Aerospace Engineering

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    Ikami, T., Kanou, K., Takahashi, K., Fujita, K., & Nagai, H. (2019). Flow field on wing surface with control surface in propeller slipstream at low reynolds number. In AIAA Scitech 2019 Forum (AIAA Scitech 2019 Forum). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2019-2159