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Aerodynamical Improvement of Delta Wing and Flapping Wing

[+] Author Affiliations
Tadateru Ishide, Kazuya Naganuma, Shinsuke Seiji, Hiroyuki Ishikawa, Ryo Fujii, Kazuo Maeno

National Institute of Technology, Kisarazu College, Kisarazu City, Japan

Paper No. AJKFluids2015-13075, pp. V01AT13A001; 6 pages
doi:10.1115/AJKFluids2015-13075
From:
  • ASME/JSME/KSME 2015 Joint Fluids Engineering Conference
  • Volume 1A: Symposia, Part 2
  • Seoul, South Korea, July 26–31, 2015
  • Conference Sponsors: Fluids Engineering Division
  • ISBN: 978-0-7918-5721-3
  • Copyright © 2015 by JSME

abstract

Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study are researching the aerodynamic improvement of delta wing and flapping wing in low Reynold’s number region to develop an applicative these air vehicle. Various configurations of Leading Edge Flap (LEF) are used to enhance the aerodynamic characteristics in the delta wing. The six kind of elliptical wings made of stainless steel are used in the flapping wing. The effects of flapping amplitude and wing configuration regarding the aerodynamic characteristics are investigated in detail. The fluid force measurement by six component load cell and PIV analysis are performed as the experimental method. In the flapping wing experiment, the simultaneous measuring of the fluid force measurement and PIV analysis is tried by using the trigger signal from the encoder attached to the flapping model. The relations between the aerodynamic superiority and the vortex behavior around the models are demonstrated.

Copyright © 2015 by JSME
Topics: Wings

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