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ANALISIS KARAKTERISTIK AERODINAMIKA AIRFOIL NACA 0012 DENGAN MENGGUNAKAN SOFTWARE BERBASIS COMPUTATIONAL FLUID DYNAMIC (CFD)

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Research referring to the airfoil technology development as one important part of aerodynamics has been widely applied. Characteristics of airfoil depending of many things, so it can be said that the each airfoil has a speciflc use. In this research, be analyzed of aerodynamics characteristics of airfoil of NACA 0012 using a Software based on Computational Fluid Dynamic (CFD). Purpose of this analysis is to examine the distribution of pressure and velocity around the airfoil, and to investigate the relationship between the coefficient of lift (CL) and coefficient of drag (Cd) againts angle of attack (a). Angle of attack is used,0°, 4°, 8°, 12°, and 16°. From the results of simulation for a range of angle of attack, obtained the largest average pressure of the fluid flowing over the surface of the airfoil at angle of attack in 0° about 101.316,043 Pa, while the largest average pressure of lower surface of the airfoil at angle of attack in 4° about 101.316,269 Pa. For the largest average velocity of fluid flowing over the surface of the airfoil at angle of attack in 8° about 13,0666 m/s, as also on the lower surface of the airfoil at angle of attack in 8 about 12,2632 m/s. In addition, it can be concluded that the higher the value of the angle of attack, the greater CL and CD will be. And the biggest seen in the angle of attack in 16° is CL = 0,25392 and CD = 0,06384.

Availability
Inventory Code Barcode Call Number Location Status
1407002598T158166T1581662014Central Library (References)Available but not for loan - Not for Loan
Detail Information
Series Title
-
Call Number
T1581662014
Publisher
Indralaya : Prodi Teknik Mesin, Fakultas Teknik Universitas Sriwijaya.,
Collation
xvi, 49 hlm. : ilus. ; tab. ; 28 cm
Language
Indonesia
ISBN/ISSN
-
Classification
629.130 7
Content Type
Text
Media Type
-
Carrier Type
-
Edition
-
Subject(s)
Prodi Teknik Mesin
Computational fluid dynamics
Aerodinamika Airfoil
Specific Detail Info
-
Statement of Responsibility
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No other version available

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