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

ISSN Print: 2152-5102
ISSN Online: 2152-5110

International Journal of Fluid Mechanics Research

DOI: 10.1615/InterJFluidMechRes.2018025530
pages 427-439


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
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


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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