Numerical Simulations Of Transonic Wingtip

dc.contributor.author	Chanrith, Suparat	en_US
dc.date.accessioned	2014-03-12T23:48:46Z
dc.date.available	2014-03-12T23:48:46Z
dc.date.issued	2014-03-12
dc.date.submitted	January 2013	en_US
dc.identifier.other	DISS-12479	en_US
dc.identifier.uri	http://hdl.handle.net/10106/24075
dc.description.abstract	This report presents numerical simulations using ANSYS FLUENT for a NACA 0012 wing both in two- and three-dimensional cases to compare with an experimental data. This comparison also allowed for any wall interference in wind tunnels to be examined. Moreover, the report also presents numerical simulation of a NACA 0012 wingtip. The simulations were conducted at Mach 0.5, 0.7, 0.75, and 0.8 at various chord Reynolds number and the angle of attack of 0, 2, 4, and 5. The numerical andexperimental data were in good agreement for the full wing and the wingtip cases.	en_US
dc.description.sponsorship	Lu, Frank	en_US
dc.language.iso	en	en_US
dc.publisher	Aerospace Engineering	en_US
dc.title	Numerical Simulations Of Transonic Wingtip	en_US
dc.type	M.S.	en_US
dc.contributor.committeeChair	Lu, Frank	en_US
dc.degree.department	Aerospace Engineering	en_US
dc.degree.discipline	Aerospace Engineering	en_US
dc.degree.grantor	University of Texas at Arlington	en_US
dc.degree.level	masters	en_US
dc.degree.name	M.S.	en_US