| dc.identifier.citation | Anderson. John D, Jr. 2007. Fundamental of Aerodyanims, Fourth Edition. Mc Graw Hill. Higher Education. New York. Casmara dan S. Wiriadidjaja, 2008, Efek Ground board Terhadap Aerofoil GAW, Jurnal Saint dan Teknologi BPPT, Jakarta. http://www.iptek.net.id/ind/?mnu=8&ch=jsti&id=243 Dugdale, R.H., 1986, Mekanika Fluida (Terjemahan), Penerbit Erlangga, Jakarta. Djojodihardjo, Harijono, 1983, Mekanika Fluida, Penerbit Erlangga, Jakarta Hakim, Azki. 2007. Kronologis Teknis Perkembangan Airfoil. http://aeroblog.wordpress.com/ 2007/II/22/ Kronologis-Teknis-Perkembangan-Airfoil/ Harahap, Yudiansah, Dkk. 2003.Analisa Karakteristik Distribusi Tekanan dan Kecepatan Pada Bodi Aerodinamika Airfoil Dengan Metoda Panel Dalam Fenomena “Flow Around Body”. Institut Teknologi Sepuluh November Suirabaya.Surabaya. http://puslit.petra.ac.id/journals/mechanical/ Giles, Ranal V. Soemitro, Herman W. 1993. Mekanika Fluida & Hidraulika, Edisi kedua (SIMetrik). Erlangga. Jakarta. Nakayama, Yasuki, dkk. 1999. Introduction to Fluid Mechanics. Butterworth-Heinemann. Oxford. R. Munson, Bruce, dkk. 2002. Mekanika Fluida jilid 2. Erlangga. Jakarta. Tjitro, Soejono, Dkk. 1999. Perbaikan Karakteristik Aerodinamika pada Kendaraan Niaga. Universitas Kristen Petra. Jakarta. Yusmanto, Arif, 2008. Studi Karakteristik Distribusi Tekanan Dan Kecepatan Disekeliling Airfoil dengan Solid Works. Universitas Muhammadiyah Surakarta. Surakarta. | en_US |
| dc.description.abstract | In the past, for making and investigating performance of airfoil should be
conducted by trial and error, and often a lot of materials waste. Since every time, if
we would like to change of the model, we have to produce new model first for doing
next investigation. Beside that, for testing the airfoil should be physically done in
the wind tunnel, it is not very easy to get information of pressure and velocity
distribution accurately. Now adays, it can be done computationally, faster and
cheaper by using both of open sources and commercial software. The aim of this
research is to investigate the characteristics of airfoil performance. It covers the
pressure distribution, velocity around the airfoil, and visualization of trajectories.
Comparison between symmetric airfoil NACA-0012 and asymmetric airfoil NACA-
2410 performance will be explained, especially relationship between CL, CD versus a
computationally. Experiment is preceded by making of symmetric airfoil model as
well as asymmetric airfoil model by using design foil open source software, and then
for adjusting angle of attach was assisted by the AutoCAD software, after that, meshing
and solving process to be done in the Solid Work Cosmos Flow software 2007. Analysis
covers distribution of pressure, velocity and trajectories simulation. The result of the
research shows, that increasing of angle of attach will be followed by increasing of lift
coefficient polynomially, other than coefficient lift is drag coefficient which proportional
with angle of attach. However, it can be seen that NACA-0012 has the higher coefficient
of lift and drag coefficient than NACA-2410. These patterns has also be compared
with U.S Department of Transportation Federal Aviation document, apparently there
has similar trend each others | en_US |
