High Swept-Back Delta Wing Flow

Thi Kim Dung Hoang; Phu Khanh Nguyen; Yoshiaki Nakamura

doi:10.4028/www.scientific.net/AMR.1016.377

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HomeAdvanced Materials ResearchAdvanced Materials Research Vol. 1016High Swept-Back Delta Wing Flow

High Swept-Back Delta Wing Flow

Abstract:

In this study, an experimentally and numerically investigation was carried out to obtain characteristics (lift force, drag force ...) on 74.5 degree Delta wing. The experiment tests were conducted at Hanoi University of Science and Technology low-speed wind tunnel facility, whereas the numerical tests were performed using the commercial computational fluid dynamics software ANSYS/FLUENT. The apparition of the vortices upon the Delta wing caused the negative pressure distribution on the wing which reached a maximum absolute value at the vortex core. The characteristics of high swept-back Delta wing were investigated at air velocity of 10 m/s and attack angle of 20 degree in changing the rolling angle of the wing from 0 to 20 degree.

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Periodical:

Advanced Materials Research (Volume 1016)

Pages:

377-382

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.1016.377

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Online since:

August 2014

Authors:

Thi Kim Dung Hoang*, Phu Khanh Nguyen, Yoshiaki Nakamura

Keywords:

Delta Wing, High Swept-Back Angle, Low Speed, Rolling Angle, Vortex

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* - Corresponding Author

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