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

2013 ◽  
Vol 315 ◽  
pp. 181-185
Author(s):  
Fatimah Yusop ◽  
Bambang Basuno ◽  
Zamri Omar
Keyword(s):  
Parametric Study ◽  
Outer Boundary ◽  
Computer Code ◽  
Tvd Scheme ◽  
High Order Scheme ◽  
Flow Past ◽  
Symmetrical Model ◽  
Flow Domain ◽  
Runge Kutta ◽  
Naca 0012

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.

scholarly journals Computational study of flow around a NACA 0012 by using Roe FVM scheme and davis-yee TVD scheme

2019 ◽  
Vol 16 (2) ◽  
pp. 1018
Author(s):  
Fatimah Yusop ◽  
Zamri Omar ◽  
Bambang Basuno ◽  
Nik Normunira Mat Hassan
Keyword(s):  
Mach Number ◽  
Numerical Scheme ◽  
Computational Study ◽  
Pressure Coefficient ◽  
Flow Analysis ◽  
Computer Code ◽  
Tvd Scheme ◽  
Finite Volume Scheme ◽  
Airfoil Surface ◽  
Naca 0012

<p>Currently CFD had been considered as an important tool for solving engineering problems. The application of CFD had been used intensively in aircraft industries in design a new aircraft or in the effort of improvement on the exiting aircraft. In term of CFD computer code, the CFD code differs with any others may due to the difference in the numerical scheme have been used. Therefore, the present work presents the comparison result between two developed computer codes with ANSYS-FLUENT software to the case of transonic steady flow past through airfoil NACA 0012. The first computer code used a finite difference method with numerical scheme according to Davis-Yee TVD scheme. Meanwhile, the second computer code used a Roe’s cell centre finite volume scheme. The flow analysis is carried out at two Mach number, M (0.65 &amp; 0.8). Each Mach number applied to two different angles of attacks (0° &amp; 5°).  The flow domain discretized by use of C-topology with 193x63 grid points. The comparison in term of the pressure coefficient, along the airfoil surface are presented. From the result, indicated that developed computer code is able to capture the presence of shock wave in the flow field.</p>

Application of Total Variation Diminishing for 1D Nozzle Problem

2013 ◽  
Vol 393 ◽  
pp. 872-877
Author(s):  
Fatimah Yusop ◽  
Bambang Basuno ◽  
Zamri Omar
Keyword(s):  
Differential Equation ◽  
Fluid Dynamics ◽  
Partial Differential Equation ◽  
Total Variation ◽  
Tvd Scheme ◽  
Total Variation Diminishing ◽  
Variation Diminishing ◽  
Computational Fluid Dynamics Cfd ◽  
Runge Kutta ◽  
Central Scheme

Computational fluid dynamics (CFD) is very widespread use every day as a tool in fluid flow analyses. In order to solve the Partial Differential Equation (PDE), there are few approach been introduced. The total variation diminishing (TVD) is a most popular scheme which is usually used in combination with other scheme. Therefore, this study develops CFD code by using Runge-Kutta which based on combination of central scheme and TVD scheme. Comparison was done through purely Runge-Kutta and after implemented TVD. The result shows that combination of Runge-Kutta and TVD approach are more stable as compared to purely Runge-Kutta approach.

Long-Term Radioactivity Release from Solidified High-Level Waste - Part II Parametric Study of Waste form Properties, Temperature and Time

1982 ◽  
Vol 15 ◽  
Author(s):  
Friedrich K. Altenhein ◽  
Werner Lutze ◽  
Rodney C. Ewing
Keyword(s):  
Parametric Study ◽  
Computer Code ◽  
Salt Dome ◽  
Waste Form ◽  
Glass Block ◽  
High Level Waste ◽  
Surface Layers ◽  
History Of ◽  
High Level

The computer code QTERM has been used to calculate the total released activity from a single glass block when in contact with brine in a salt dome repository as a function of: (1) waste form properties, (2) leaching mechanisms, (3) retention or precipitation of specific radionuclides in surface layers, (4) thermal history of the repository and (5) decreasing activity as a function of time.

A Parametric Study of Conjugate Heat Transfer of Solar Chimney

2009 ◽  
Author(s):  
J. Arce ◽  
J. P. Xaman ◽  
G. Alvarez ◽  
M. J. Jime´nez ◽  
M. R. Heras
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Parametric Study ◽  
Solar Irradiance ◽  
Natural Ventilation ◽  
Numerical Study ◽  
Ambient Air ◽  
Computer Code ◽  
Solar Chimney ◽  
Conservation Equations

Recently, new buildings are being designed considering natural sources such as natural ventilation as a passive technique. Solar chimneys are among those techniques of passive ventilation systems in buildings, to enhance the air quality and some times the thermal comfort. In this work, a numerical study of a solar chimney for forced ventilation is carried out. Also a parametric study varying the ambient air temperature, the solar irradiance and Reynolds number is considered. The dimensions of the solar chimney are 4.0 m high, and 0.35 m deep, the absorber surface of the solar chimney was 0.15 m thick of reinforced concrete. The conservation equations of mass, momentum, energy and two turbulence equations are solved under some simplifications such as: 2-D, incompressible, steady state turbulent air flow and conjugated heat transfer (conduction, forced convection and radiation). k-ω turbulent model was implemented and finite volume technique was applied to solve the conservation equations. In order to guarantee the right performance of the computer code, it was reduced to cases reported in the literature and verified; also, it was validated with an experiment. The variation of ambient temperature, solar irradiance and Reynolds number are analyzed in the parametric study. The heat transfer correlations for total Nusselt number (convective plus radiative) are introduced. From the results, it was found that the heat transfer increases as the Reynolds number increases for the hot surface of the solar chimney.

Characteristics of Flow Past a Symmetric Airfoil at Low Reynolds Number: A Nonlinear Perspective

2012 ◽  
Author(s):  
M. Saif Ullah Khalid ◽  
Imran Akhtar
Keyword(s):  
Reynolds Number ◽  
Period Doubling ◽  
Nonlinear Behavior ◽  
Phase Portraits ◽  
Aerodynamic Forces ◽  
Flow Past ◽  
Time Histories ◽  
Lift And Drag ◽  
Naca 0012 ◽  
Even Harmonics

Flow separation in airfoils have been extensively studied to analyze the underlying physics of the phenomenon. The phenomenon being nonlinear requires tools to reveal various features involving stall, bifurcation, and transition to chaos. In this study, we perform numerical simulations of the flow past a symmetric airfoil (NACA-0012) at 1,000 Reynolds number to compute the aerodynamic forces at different angles of attack (α). The time histories and spectral analysis reveal important features of nonlinear behavior in the flow around the airfoil. We find that the steady state temporal solutions for aerodynamic forces; lift and drag, contain both odd and even harmonics which indicate the presence of quadratic as well as cubic nonlinearity in the system. These results also help to understand nonlinear behavior of the system as a function of α. Considering the angle of attack for airfoil as a control parameter, we observe that to achieve the static stall, flow becomes chaotic adopting a route through period-doubling and quasi-periodic regimes. Using phase portraits and Poincare maps between the states of the system, period-doubling is observed in this nonlinear system at α = 22° leading to chaos at α = 27°.

Comparison Results between MacCormack Scheme and Steger Warming Scheme for the Case of Supersonic Flow Pass through Divergent Nozzle

2013 ◽  
Vol 315 ◽  
pp. 268-272
Author(s):  
Hasan Taher M. Elkamel ◽  
Abobaker Mohammed Alakashi ◽  
Bambang Basuno
Keyword(s):  
Unsteady Flow ◽  
Euler Equation ◽  
Flow Problem ◽  
Flow Behavior ◽  
Steady State Solution ◽  
Computer Code ◽  
Hyperbolic Type ◽  
Tvd Scheme ◽  
Comparison Results ◽  
Pass Through

The present work focuses on the development of computer code which allow the engine designer investigate the flow behavior through a divergent nozzle. The flow is assumed as quasi one dimensional and steady inviscid compressible flow. In other word the flow is governed by compressible Euler equation depending on the local Mach number. Solving such a mixed type of equation is difficult. The boundary between hyperbolic and elliptic region is not clear. To avoid such difficulty can be done through treating a steady flow problem as unsteady flow problems with the boundary condition is fixed with respect to time. As unsteady flow problem, the Euler equation becomes hyperbolic type of partial differential equation with respect to time. This approach allows one to solve the unsteady flow problem goes to a steady state solution. There are various methods can used for solving hyperbolic type of equation, such as MacCormacks scheme, Steger Warmings scheme, Beam Warmings Scheme and TVD Scheme. The present work used MacCormacks scheme and Steger Warming scheme will be used to investigate the flow behavior through a divergent nozzle. Comparison with analytic solution shows that Steger Warmings scheme gives a better result than MacCormacks scheme.

Ballooning Deformation of Zircaloy-4 Fuel Sheath

2014 ◽  
Vol 136 (3) ◽  
Author(s):  
Mohd. Kaleem Khan ◽  
Manabendra Pathak
Keyword(s):  
Internal Pressure ◽  
Parametric Study ◽  
Circumferential Strain ◽  
Experimental Studies ◽  
Computer Code ◽  
Inert Atmosphere ◽  
Experimental Setup ◽  
Heating Rates ◽  
Clad Tube ◽  
Internal Pressures

In this paper, both experimental and analytical investigations have been conducted to investigate the fuel sheath (also known as clad tube) ballooning deformation and subsequent bursting. The work has been performed to simulate ballooning deformation of fuel sheaths under different heating rates and internal pressures in an inert atmosphere. An experimental setup has been designed to capture the temperature, pressure, and wall displacement data during the ballooning deformation of the sheath specimen. Also, a computer code in MATLAB has been developed to compute the stresses and strains at the ballooning site of the fuel sheath. The developed model has been validated with present and past experimental studies. A parametric study has also been conducted to study the effect of internal pressure, heating rate, and sheath dimensions on hoop or circumferential strain.

scholarly journals On a Study of Flow Past Non-Newtonian Fluid Bubbles

2021 ◽  
Vol 16 ◽  
pp. 74-86
Author(s):  
T. S. L. Radhika ◽  
T. Raja Rani
Keyword(s):  
Fluid Flow ◽  
Coordinate System ◽  
Newtonian Fluid ◽  
Outer Region ◽  
Considerable Effect ◽  
Governing Equations ◽  
Spherical Coordinate ◽  
Flow Past ◽  
Flow Domain ◽  
High Viscous Fluid

In the current work, we aim at finding an analytical solution to the problem of fluid flow past a pair of separated non-Newtonian fluid bubbles. These bubbles are assumed to be spherical and non-permeable with the non-Newtonian fluid, viz. the couple stress fluid filling their interior. Further, the bubbles are presumed to be static in the flow domain, where a Newtonian fluid streams past these bubbles with a constant velocity (U) along the negative x-direction. We developed a mathematical model in the bipolar coordinate system for the fluid flow outside the bubbles and the spherical coordinate system inside the bubbles to derive a separable solution for their respective governing equations. Furthermore, to evaluate the model's applicabilities on the industrial front, the data on some widely used industrial fluids are given as inputs to the model, such as density, the viscosity of air or water for the fluid flow model developed for the region outside the fluid bubbles and the data on Cyclopentane or DIDP (non-Newtonian) for that within the bubbles. Some interesting findings are: the pressure in the outer region of the bubbles is higher when filled with low viscous industrial fluid, Cyclopentane, than a high viscous fluid, DIDP. Furthermore, an increase in the viscosity of Cyclopentane did not alter the pressure distribution in the region outside the bubbles. However, there is a considerable effect on this pressure in the case of DIDP bubbles.

scholarly journals Development of a method for geometric modeling of centrifugal compressor impellers

2021 ◽  
Vol 1 (1 (109)) ◽  
pp. 35-42
Author(s):  
Valeriy Borisenko ◽  
Serhiy Ustenko ◽  
Iryna Ustenko ◽  
Kateryna Kuzma
Keyword(s):  
Centrifugal Compressor ◽  
Cylindrical Surface ◽  
Geometric Modeling ◽  
Outer Boundary ◽  
Computer Code ◽  
Outer Radius ◽  
Digital Information ◽  
Blade Profile ◽  
Centrifugal Compressors ◽  
Curvature Distribution

The practice of designing centrifugal compressors in which impellers are the main components shows that there are reserves for their further improvement. One of the main reserves consists in improving flow conditions for the compressed medium in the compressor setting and, above all, in the impeller. A method of geometric modeling settings of the impellers of centrifugal compressors was proposed which involves the construction of meridional boundaries of impellers and the blade profile on an involute of the cylindrical surface of the outer radius of the impeller. The blade is represented by ruled surfaces. The outer boundary of the impeller is described by a curve in natural parameterization using cubic dependence of curvature on the arc length. Dependences and length of the arc are determined in the process of modeling the boundary based on the set source data. The problem is solved by minimizing deviations of intermediate curves from the boundary endpoint. The inner boundary is obtained as an envelope of circles inscribed in the meridional channel of the impeller. Radii of the circles are determined taking into account the flow areas of the channel. The midline of the blade profile on an involute of the cylindrical surface of the outer radius of the impeller is modeled using a curve that is presented in natural parameterization with quadratic law of curvature distribution. A computer code was developed in the Fortran Power Station programming environment that visualizes the obtained numerical results graphically on a computer display in addition to digital information on the modeled boundaries and the blade profile. Graphical results were presented. They confirmed the efficiency of the proposed method of modeling the settings of centrifugal compressor impellers. The method can be useful to offices involved in the design of centrifugal compressors

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