The Effects Of NACA 0012 Airfoil Modification on Aerodynamic Performance Improvement and Obtaining High Lift Coefficient and Post-Stall Airfoil

dc.contributor.author	Soğukpınar, Hacı
dc.date.accessioned	2024-02-15T06:28:19Z
dc.date.available	2024-02-15T06:28:19Z
dc.date.issued	2018
dc.identifier.issn	0094-243X
dc.identifier.uri	http://dspace.adiyaman.edu.tr:8080/xmlui/handle/20.500.12414/4880
dc.description.abstract	In this study, aerodynamic performances of NACA 0012 airfoils with distinct modification are numerically investigated to obtain high lift coefficient and post-stall airfoils. NACA 0012 airfoil is divided into two part thought chord line then suction sides kept fixed and by changing the thickness of the pressure side new types of airfoil are created. Numerical experiments are then conducted by varying thickness of NACA 0012 from lower surface and different relative thicknesses asymmetrical airfoils are modified and NACA 0012-10, 0012-08, 0012-07, 0012-06, 0012-04, 001203, 0012-02, 0012-01 are created and simulated by using COMSOL software.	tr
dc.language.iso	en	tr
dc.publisher	AMER INST PHYSICS	tr
dc.title	The Effects Of NACA 0012 Airfoil Modification on Aerodynamic Performance Improvement and Obtaining High Lift Coefficient and Post-Stall Airfoil	tr
dc.type	Article	tr
dc.contributor.authorID	0000-0002-9467-2005	tr
dc.contributor.department	Adiyaman Univ, Vocat Sch, Dept Elect & Energy,	tr
dc.identifier.volume	1935	tr
dc.source.title	TURKISH PHYSICAL SOCIETY 33RD INTERNATIONAL PHYSICS CONGRESS (TPS33)	tr