1D Unsteady Compressible Navier-Stokes using MATLAB

https://projects.skill-lync.com/projects/Prandtl-Meyer-Shock-problem-80219

https://projects.skill-lync.com/projects/Prandtl-Meyer-Shock-problem-80219

https://projects.skill-lync.com/projects/Conjugate-Heat-Transfer-simulation-PipeFlow-00011

 *********** Comments by Grader ************EXCELLENT JOB !!!!Where is an animation ?Create an animation and upload it on Youtube link and paste the link in the project page.Marks here are deducted for the above mentioned reasons.SUGGESTION : If you have any doubts please ask us on WATS APP or raise a ticket on FRESHDESK…

 *********** Comments by Grader ************EXCELLENT JOB !!!!Where is an animation ?Create an animation and upload it on Youtube link and paste the link in the project page.Marks here are deducted for the above mentioned reasons.SUGGESTION : If you have any doubts please ask us on WATS APP or raise a ticket on FRESHDESK…

https://projects.skill-lync.com/projects/Conjugate-Heat-Transfer-simulation-PipeFlow-00011

In this project, Couette flow ( flow of a viscous fluid in the space between two surfaces, one of which is moving tangentially relative to the other) is being studied.The main objective of the project is to discretize the Navier-Stokes equation using Finite Difference method, and solve them numerically using SIMPLE (Semi-Implicit…

In the current project a Shock wave tube or a Riemann tube problem is being studied.This is aparticularly useful case as it simulates a shock wave, expansion wave and discontinuity.From a numerical point of view, this problem constitutes, since the exact solution is known, aninevitable and difficult test case for any numerical…

The main objective of this project is to design a 4-stage- Axial compressor with inlet guide vane, having constant tip diameter and using free vortex distribution i.e. swirling flow with constant angular momentum. Also, for the same volume flow rate and inlet conditions, results for the two different fluids- Air and Hydrogen…

https://projects.skill-lync.com/projects/Prandtl-Meyer-Shock-problem-80219

 https://projects.skill-lync.com/projects/Backward-Facing-Step-using-Converge-Studio-72118

1. A=[ 1,2,3,4,5]-This means numbers-1,2,3,4,5 are saved in an array-\'A\' variable. Array:1-row X 5-columns. 2.B=[1;2;3;4;5]- This means numbers will be saved in an array-\'B\'. Array: 5-rows X 1-column. 3. C=A*B\'. This wont work because B\' is B transpose which will change B into 1X5 matrix. And we cannot multiply two…

https://projects.skill-lync.com/projects/Shock-tube-simulation-project-60595

Boundary conditions and initial conditions dictate particular solutions to be obtained from Partial differential equations. Though the equations of fluid flow is same -Navier stokes equation but these boundary conditions actually drive the equations to actual solution.  For example no slip condition at boundary, will…

1. τ = μ du / dy ( τ- Shear Stress;  μ-dynamic  viscosity; du = unit velocity;dy = unit distance between layers) μ=τ*dy/du (Units,μ= (N/m^2)* m/(m/s)  )=N s/m^2=kg/ms Kinematic Viscosity= Dinematic viscosity/p  (p=density) v(kinematic viscosity)= v/p= N-s/m^2/…

clear all close all clc %n1=number of moles of C for alkane n1=1:1:5; %ar1= stoechometric coefficient for alkane ar1= (3*(n1)+1)/2; %n2=number of moles of C for alkene n2=1:1:5; %ar2= stoechometric coefficient for alkene ar2=3*n2/2; %n3=number of moles of C for alkyne n3=1:1:5; ar3=((3*n3)-1)/2; %ar3=stoechometric coefficient…

1. Divergence: It is  the outward flux of the quantity(vector field) through a closed surface is equal to the volume integral of the divergence over the region inside the surface.   Divergence = ∇.    (  =x i +y j +zk .  ,∇=) Result is a…

clear all close all clc g=9.8; L=1; m=5; w=g/(L*m); t=[0 200]; theta0=[45 0]; [t,theta]=ode45(@(t,theta)pend_function(t,theta,w),t,theta0); thetad=theta(:,1); %axis O=[0 0]; axis(gca,\'equal\'); axis([-1 1 -1 0.8]); grid on; %loop for i=1:length(t); Origin=viscircles(O,0.02); P=[L*sind(thetad(i)) -L*cosd(thetad(i))]; circle_P=viscircles(P,0.04);…

This projects summarizes the CFD simulation carried out for a shocktube problem using Converge Studio Package and post-processingi in Paraview. In this simulation, we have used this feature- "Events" used in converge package. This feature help us to simulate the similar physical conditions -- like breaking a diaphragm…

1. Eigen value of A, as per code-   2.Spectral radius of identity matrix of A as per code: -Jacobi method:0.0487 -Gauss-Siedel: 0.0386 -SOR: 0.0584 3. System of equation was solved using : -Jacobi method- number of iteration-20 -Gauss_siedel method- number of iteration-7 -SOR-method with relaxation factor 1.1- number…

clear all close all clc x=pi/3; dx= linspace(pi/4,pi/4000,50); analytical_solution=(x^3*(cos(x))-sin(x)*3*x^2)/x^6; for i=1:length(dx) central_differencing= ((sin(x+dx(i))/(x+dx(i))^3)-(sin(x-dx(i))/(x-dx(i))^3))/(2*dx(i)); second_order_error(i)=second_order_discretization(x,dx(i)); forward_differencing= ((sin(x+dx(i))/(x+dx(i))^3)-(sin(x)/x^3))/(dx(i));…

Flow simulation was setup up using Converge Studio, and post processing was carried out in Paraview. Inlet Reynold number-10000 Inflow velocity- 5m/s Turbulence model- K-epslon model Super-cycling modelling was carried out for overcoming time-scale disparity. In super-cycling, the fluid solver is frozen periodically while…

Shockwave : It is characterized by an abrupt, nearly discontinuous change in pressure, temperature and density of the medium, when a wave moves faster than the local speed of sound in a fluid. Based on characterization it can be of many types. For example based on angle: Normal shock, Oblique shocks, Bow shocks.  …

https://projects.skill-lync.com/projects/Transient-simulation-of-flow-over-a-throttle-body-10401

Transient analysis is carried to visualize the flow over a throttle body in an elbow pipe. Turbulence model---> RNG K-epslon Software Package- Converge Studio and Paraview Valve is rotated at 25 degrees from 0 to 2 seconds, then from 4 seconds to 8 seconds it is returned back to its original position.   Velocity…

https://projects.skill-lync.com/projects/Steady-state-simulation-of-flow-over-a-throttle-body-18551

This project summarizes the CFD simulation using RNG k-epslon turbulence model for steady flow simulation over a throttle body through an elbow pipe using Converge Studio Package: Mesh: Near the valve, grid embedding is applied:   Post-Processing of Results (using Paraview) Velocity visualization in elbow at steady…

Case setting was done using Converge studio for this project and post processing was carried out in paraview : 1. 2e-3: Grid: Velocity Plot: Pressure plot: Velocity vectors:   2. 1.5 e-3 grid size Grid: Velocity plot:   Pressure plot:   Velocity vector:   3. 1e-3 grid size Grid:   Velocity plot:…

https://projects.skill-lync.com/projects/Channel-flow-simulation-using-CONVERGE-CFD-93170

CFD simulation was carried out on Channel flow using Converge package. Converge case setup was done using Converge, and post processing was carried out both using converge and Paraview. Following are the results: 1. Base grid: 2e-4m Grid: Velocity_visualization in Paraview:   Pressure visualization in Paraview  …

Based upon the different grade factors chosen for analysis, following results were obtained: -Number of cells in x direction-->200 -Number of celles in y direction-->10 -Meshing was graded such that the dx is smaller near all walls. For running the simulation, dt was changed for all the 3 grades, as with decrease…

Calculations were carried out using conservation and non-conservation form of Navier-Stokes Equation. -Non-conservation form: Number of cycles: most of the variations in values occurs in the initial number of time steps. But at most till 400-500 iterations, values dont change that much. And after about 1000 iterations,…

First picture compares 4 plots, with the above given conditions: n=80 and c=1 The red line shows the initial boundary condition and blue line shows the final value at t=0.4 seconds: Scheme used is explicit. And based on the results it shows it fails with higher values of dt, at dt=0.1. Now next I used implicit scheme to…

The first picture compares 4 plots  for C=1 & time-0.4 seconds, comparing original and final velocities for different values of n. Solving scheme used is explicit. The Red part is the original velocity profile or initial boundary condition. Based on the results, the solution seems to be stable till n=80, but as…