Flow-control experiment around half-span wing model for dbd-pa application on uav

Satoshi Sekimoto, Koji Fujita, Kozo Fujii

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Citation (Scopus)

Abstract

Assuming installation of a dielectric-barrier-discharge plasma actuator (DBD-PA) on a small fixed-wing 2-m-span UAV, a wind-tunnel experiment using a NACA23015 three-dimensional wing model with a chord-length of 200 mm and an aspect ratio of 3.5 was conducted. DBD-PA was installed at the leading edge. Flow-control capability was evaluated by time-averaged pressure measurement with changing the span-wise DBD-PA length. Results show that the condition of the controlled flow field changes abruptly around the span-wise DBD-PA length of 80 %, rather than changes linearly. This result is important knowledge for the installation of DBD-PA on a fixed-wing UAV.

Original languageEnglish
Title of host publicationAIAA Scitech 2021 Forum
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages1-14
Number of pages14
ISBN (Print)9781624106095
Publication statusPublished - 2021
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online
Duration: 11 Jan 202115 Jan 2021

Publication series

NameAIAA Scitech 2021 Forum

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
CityVirtual, Online
Period11/01/2115/01/21

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