CFD analysis of flow characteristics of NACA0012 airfoil using SU2
Keywords:NACA0012, SU2, angle of attack, CFD
This paper presents the CFD analysis of the flow over a NACA 0012 Airfoil at different Mach number and at different angle of attacks using SU2 open source CFD code. The Mach number examined were 0.1, 0.3, 0.5, while the angle of attack(AOA) ranged from 5 to 15 degrees in 5 degree increments. This work was initiated to create an awareness of su2 software through computational simulation. The characteristics of the naca0012 airfoil operating at different mach number and at different AOA is analyzed by predicting the lift and drag measurements. Low Reynolds number is selected for the analysis. The Euler solver of open source CFD code is chosen for laminar flow analysis over naca0012 airfoil. The simulations are predicting the lift to drag ratio of naca0012 airfoil for specific conditions accurately.
F. Palacios, M. R. Colonno, A. C. Aranake, A. Campos, S. R. Copeland, T. D. Economon, A. K. Lonkar, T. W. Lukaczyk, T. W. R. Taylor, and J. J. Alonso (2013), "Stanford University Unstructured (SU2): An open-source integrated computational environment for multi-physics simulation and design", AIAA Paper 2013-0287.
F. Palacios, T. D. Economon, A. C. Aranake, S. R. Copeland, A. K. Lonkar, T. W. Lukaczyk, D. E. Manosalvas, K. R. Naik, A. S. Padron, B. Tracey, A. Variyar, and J. J. Alonso (2014), "Stanford University Unstructured (SU2): Opensource analysis and design technology for turbulent flows", AIAA Paper 2014-0243.
Manish K. Singh, V. Ramesh and N. Balakrishnan (2015), "Implicit scheme for meshless compressible Euler solver", Engineering Applications of Computational Fluid Mechanics, 9:1, 382-398, DOI: 10.1080/19942060.2015.1048621.
Eleni C. Douvi, Athanasios I. Tsavalos, Dionissios P. Margaris, CFD calculation of the flow over a NACA 0012 airfoil, Fluid Mechanics Laboratory University of Patras, Department of Mechanical Engineering and Aeronautics 26500 Patras, Greece, July2010.