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 contribution

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: 2021 Jan 112021 Jan 15

Publication series

NameAIAA Scitech 2021 Forum

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
CityVirtual, Online
Period21/1/1121/1/15

ASJC Scopus subject areas

  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Flow-control experiment around half-span wing model for dbd-pa application on uav'. Together they form a unique fingerprint.

Cite this