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Meeting 26/01/12


Dr. Chung: can you bring some graphs next time

Running on Steady mode

Using Pressure difference

Dr Chung: how is your grid independence going?

Dominic: It is taking a long time, maybe a more course mesh should be used

Adrian: You can save time by saving the result from the last grid independence test

Then refine the mesh and simulate again.

Dr. Chung: can you send around your results to the 3D group



Done a medium flow analysis to see the jet

Done cross sections around the narrowest part to compare how the speed changes

Waiting for it to properly converge

This is an unsteady simulation

Lost about 4 hours of simulation in Star CCM

Wanted to do one run on each of the upper airways models

To see how the flow changes across the three

And then go back to the particle simulation

Dr Chung: So the simulations should be the same between you and dominic


Dr Chung: have you worked out the Reynolds number?

Dr Chung: Pressure difference might be better for you

Need to choose the target speed to choose our target Reynolds number

Then you can increase the pressure difference and eventually we will have about 1000 reynolds number and hence turbulent



Getting some interesting grid independence tests on the trachea and bronchioles

Whilst I am varying the base size from a minimum to a maximum, some of the intermediate base sizes output an error during the simulation

Dr. Chung: Start from your fine mesh simulations and work back from that

CFD crash course: You solve partial differential equations. We give up trying to find the true solutions as they are nearly impossible (very hard) to find.

Instead we choose discrete points in the domain. Say I don’t want to know what is inbetween those points, but if you connect the values, you will have a clear idea of what is going on. If you have enough points you can assume it will change linearly between the points

This is why you need the grid independence test to see whether that certain amount of points is enough

By choosing discrete points you change partial differential equations to a series of simultaneous equations. I.e. ten points gives you 10 equations.

With three or four equations you can re-arrange the equations with the gauss-seidel method. However with like 4 million equations you cannot do this. And so we have to use course mesh solutions to get started and then refine to get convergence.

Adrian: Using inlet velocity boundary conditions now.

Dr Chung: Because we don’t know the velocity profile, it is better to use a pressure inlet rather than a velocity inlet.

Adrian: Prism layer to base size 200%

Dr. Chung: Plot your mesh on the cross sectional areas and then see how much is covered by the prism layers. Then plot the velocity profile there and see if there are any sharp changes.

So just plot your mesh at many different locations


A paper that Tom found last term will be used to model the affect of angle changes on pressure drop.

Tom will also manually find the angle changes for select pathways of the stl file.

Tom will make a matlab model that encorporates all of the mathematical relations that we have found so far


I have been working on the algorithm

It is now all coded, however had trouble plotting the surface of the airways

I am currently trying to find the problem in the code

Charlie and Tom have been thinking about how the angle change data can be recorded to preserve the all important connectivity of the model


Daniel has been doing research

Daniel will be working with Tom to create this Matlab model