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Effect of Leading-Edge Slats at Low Reynolds Numbers

by *,† and
Aerospace Engineering Department, Embry Riddle Aeronautical University, Prescott, AZ 86301, USA
Author to whom correspondence should be addressed.
These authors contributed equally to this work.
Academic Editor: Ning Qin
Aerospace 2016, 3(4), 39;
Received: 5 August 2016 / Revised: 10 October 2016 / Accepted: 13 November 2016 / Published: 17 November 2016
(This article belongs to the Collection Unmanned Aerial Systems)
One of the most commonly implemented devices for stall control on wings and airfoils is a leading-edge slat. While functioning of slats at high Reynolds number is well documented, this is not the case at the low Reynolds numbers common for small unmanned aerial vehicles. Consequently, a low-speed wind tunnel investigation was undertaken to elucidate the performance of a slat at Re = 250,000. Force balance measurements accompanied by surface flow visualization images are presented. The slat extension and rotation was varied and documented. The results indicate that for small slat extensions, slat rotation is deleterious to performance, but is required for larger slat extensions for effective lift augmentation. Deployment of the slat was accompanied by a significant drag penalty due to premature localized flow separation. View Full-Text
Keywords: slat; slot; low Reynolds number; stall control; flow control; unmanned aerial vehicle slat; slot; low Reynolds number; stall control; flow control; unmanned aerial vehicle
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MDPI and ACS Style

Traub, L.W.; Kaula, M.P. Effect of Leading-Edge Slats at Low Reynolds Numbers. Aerospace 2016, 3, 39.

AMA Style

Traub LW, Kaula MP. Effect of Leading-Edge Slats at Low Reynolds Numbers. Aerospace. 2016; 3(4):39.

Chicago/Turabian Style

Traub, Lance W.; Kaula, Mashaan P. 2016. "Effect of Leading-Edge Slats at Low Reynolds Numbers" Aerospace 3, no. 4: 39.

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