High Swept-Back Delta Wing Flow
2014 ◽
Vol 1016
◽
pp. 377-382
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Keyword(s):
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.
2014 ◽
Vol 592-594
◽
pp. 869-873
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2019 ◽
Vol 233
(14)
◽
pp. 3621-3629
2011 ◽
Vol 78
(1)
◽
pp. 49-60
◽
2010 ◽
Vol 439-440
◽
pp. 880-883
Keyword(s):
Keyword(s):
2012 ◽
Vol 220-223
◽
pp. 1698-1702