Application of Modified 4^th Order Runge Kutta-TVD Scheme for the Flow Past through Symmetrical Model

Abstract

Computational fluid dynamics (CFD) is a well known tool to solve the fluid flow problems. In CFD analysis, the models use various types of Partial Differential Equation (PDE). The most common is hyperbolic equation. In order to solve the equation, high-order scheme is very reasonable to be applied due to the accuracy of result. So that, this study use modified Runge Kutta with Total Variation Diminishing (TVD) scheme and the model is half body airfoil (symmetrical airfoil NACA 0012). Firstly, parametric study over the size of suitable flow domain was carried out. If the length of airfoil chord is denoted by c, investigation effects on the size of flow domain is carried over the flow domain in x-direction which is 5c while in y-direction is 6c. Another two size flow domains had been used in this study are 5c×3c and 9c×3c respectively. The result shows a strong influence to the flow field solution occurred if the distance between airfoil surfaces to the outer boundary is relatively small. Through this parametric study, it had been suggested that the best way to solve the aerodynamics problem for the flow past through symmetrical airfoil by using the size of flow domain is 5c×6c. Using the same size of flow domain, it had been found that the developed computer code able to produce the result in a good agreement with ANSYS CFD-FLUENT software.

Comparison of Pressure Distribution of Naca 0012 Between CFD Code and Experimental

“…The CFD code which developed based on TVD criteria had been widely used as CFD code for aircraft aerodynamics analysis such ENSOLV, EURANUS, ZEN, EDGE, and others [3]. Others application in fluid dynamics also used TVD such for 1D nozzle problem [6,7], 2D symmetrical model [8] and many others.…”