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International Journal of Fluid Mechanics Research
ESCI SJR: 0.206 SNIP: 0.446 CiteScore™: 0.5

ISSN Imprimir: 2152-5102
ISSN En Línea: 2152-5110

Volumes:
Volumen 46, 2019 Volumen 45, 2018 Volumen 44, 2017 Volumen 43, 2016 Volumen 42, 2015 Volumen 41, 2014 Volumen 40, 2013 Volumen 39, 2012 Volumen 38, 2011 Volumen 37, 2010 Volumen 36, 2009 Volumen 35, 2008 Volumen 34, 2007 Volumen 33, 2006 Volumen 32, 2005 Volumen 31, 2004 Volumen 30, 2003 Volumen 29, 2002 Volumen 28, 2001 Volumen 27, 2000 Volumen 26, 1999 Volumen 25, 1998 Volumen 24, 1997 Volumen 23, 1996 Volumen 22, 1995

International Journal of Fluid Mechanics Research

DOI: 10.1615/InterJFluidMechRes.2018025530
pages 427-439

STUDY OF MESH INDEPENDENCE ON THE COMPUTATIONAL MODEL OF THE ROLL-UP VORTEX PHENOMENON ON FIGHTER AND DELTA WING MODELS

Setyawan Bekti Wibowo
Department of Mechanical and Industrial Engineering, Faculty of Engineering, Universitas Gadjah Mada, Yogyakarta 55281, Indonesia; Department of Mechanical Engineering, Vocational College, Universitas Gadjah Mada, Yogyakarta 55281, Indonesia
Sutrisno
Department of Mechanical and Industrial Engineering, Faculty of Engineering, Universitas Gadjah Mada, Yogyakarta 55281, Indonesia
Tri Agung Rohmat
Department of Mechanical and Industrial Engineering, Faculty of Engineering, Universitas Gadjah Mada, Yogyakarta 55281, Indonesia

SINOPSIS

A good visualization technique is needed to analyze the flow around the aircraft to see how much innovation can be made to improve the performance of a fighter. The use of water tunnel experiments is one of the solutions to getting a detailed visualization of the flow patterns that occur. However, there is some other information that is difficult to obtain qualitatively, so it requires computational fluid dynamics (CFD) techniques to extract some detailed data mainly related to the airflow around the fighter, such as the occurrence of roll-up vortex phenomena. One of the most important things to note on the use of CFD methods is the need for studies concerning the technique of meshing arrangements and the selection of constitutive equations used to ensure the results of the CFD as accurately as possible. This study will examine the accuracy of using the optimum number of cells on the mesh in obtaining convergent values of lift coefficients (Cl) on the delta wing and the fighter compared to the experimental test of a water tunnel. The results show that the coefficient of lift was converged on the mesh of more than 5 million cells with the error rate below 1%, indicating the optimum value of the mesh.

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