期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2015
卷号：4
期号：2
页码：470
DOI：10.15680/IJIRSET.2015.0402035
出版社：S&S Publications
摘要：Numerical simulation of flow past airfoils in the stalled region is a challenging problem due to variouscomplex phenomena like strong vortex dynamics, boundary layer separation due to adverse pressure gradient etc. Foraccurate numerical prediction of separated flow, correct modeling of boundary layer is essential to capture the flowdetails. In the present work 2D Computational Fluid Dynamics (CFD) analysis for flow around NACA 23024 subsonicairfoil at Reynolds number of 3 million is carried out for a range of angle of attack (0 to +20 degrees) covering boththe linear slope and stalling region using ANSYS FLUENT CFD software package. CFD analysis results are comparedwith the wind tunnel test results. The performance of Spalart-allamaras one equation turbulence model, K-epsilonturbulence model with standard wall functions is analyzed. Lift and drag coefficients measured in wind tunnel arecompared with the CFD analysis results. Deviation between wind tunnel test results and CFD analysis results in thestalled region is analyzed and accurate methodology for capturing the aerodynamic flow phenomena is established.
