Article
Version 1
This version is not peer-reviewed
Effect of Gurney Flaps on Non-Planar Wings at Low Reynolds Number
Version 1
: Received: 23 July 2024 / Approved: 23 July 2024 / Online: 24 July 2024 (16:40:26 CEST)
How to cite: Traub, L. W. Effect of Gurney Flaps on Non-Planar Wings at Low Reynolds Number. Preprints 2024, 2024071866. https://doi.org/10.20944/preprints202407.1866.v1 Traub, L. W. Effect of Gurney Flaps on Non-Planar Wings at Low Reynolds Number. Preprints 2024, 2024071866. https://doi.org/10.20944/preprints202407.1866.v1
Abstract
The effect of spanwise wing non-planarity, implemented in conjunction with a Gurney flap is presented. Testing was undertaken in a low speed wind tunnel using a rectangular wing with an aspect ratio of 3. The outer 1/3 of the wing was non-planar which took the form of dihedral or a circular arc. A 2% high Gurney flap was implemented such that it could extend over the entire span, or the planar inboard section. Loads were measured using a sting balance. The data shows that non-planarity increases the maximum lift coefficient and the wing’s lift curve slope. Gurney flap lift modulation was enhanced in the presence of non-planarity. The addition of Gurney flaps caused a greater minimum drag coefficient increment for the non-planar wings. The Gurney flaps reduced the lift dependent drag of the wings; however, the minimum drag coefficient was observed to increase. The Gurney flaps reduced the maximum lift to drag ratio (L/D) for the non-planar wings; however, the flat wing showed a small L/D increment with flap addition.
Keywords
Gurney flap; non-planar wings; low Reynolds number; wind tunnel testing; spanwise camber
Subject
Engineering, Aerospace Engineering
Copyright: This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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