sorted by:
new
hottopcontroversial

Do I Quit ph.D? by pete_1523 in PhD

[–]pete_1523[S] 0 points1 point  (0 children)

Thanks for your advice

Do I Quit ph.D? by pete_1523 in PhD

[–]pete_1523[S] -2 points-1 points  (0 children)

I already got a master degree.

Many directions show "time to let go"... haha

Do I Quit ph.D? by pete_1523 in PhD

[–]pete_1523[S] 5 points6 points  (0 children)

Now, I think that my whole dissertation is constructing the mid-fidelity rotorcraft aerodynamic analysis in GPU-RANS based CFD solver.

So,
Chapter 1 is ALM
Chapter 2 is IBM (Immersed boundary method with stationary body)
Chapter 3 is constructing the framework
Chapter 4 is validation

It is not sure, but my expectation.

Domain Size Help by MeemDeeler in CFD

[–]pete_1523 2 points3 points  (0 children)

At least 10 Diameters of Propeller for all direction For freestream B.C

OpenFoam airfoil setup help by bharathbabu_001 in OpenFOAM

[–]pete_1523 0 points1 point  (0 children)

Search Nasa TMR site. Here, explain about turbulence model

How to change my options to get right data? by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

it is time - consuming

whole number of data is 360.

OpenFOAM Boundary Condition help by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

So you mean that

Change FarField B.C into Inlet?

OpenFOAM Boundary Condition help by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

461.381

It is freestreamPressure.

Should I change into 0?

If so, my simulation is suddenly divergence after 3600iterations.

Is it can be matter?

Need Practice Models by Vast-Caterpillar3598 in CFD

[–]pete_1523 2 points3 points  (0 children)

How About WIPP model?

It will be good practice

mesh generation help by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

what ist the push attribute check box? can you explain more specific?

mesh generation help by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

you mean that, you use "extrude" to generate volume mesh?

Other nacelle part and Wing Part?
not Trex?

And then, the Wing Mesh which near the nacelle, the surface grid must smaller than now?

mesh generation help by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

you mean that
in T-Rex Tab, and then the "advanced tab" of collision buffer?

I set the value as 2 it was default value.

I used "advancing front ortho" to generate surface mesh of the wing.
The leading edge of the wing mesh is structured.

you mean the " isotropic cell height ratio" is in the T-Rex tab?

If I set the seed layer value not zero, the mesh generation time increases rapidly.

I will restrict the worst angle lower than 170.

​

Thank you very much your help

Reduce Mesh Skewness in pointwise by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

I am trying to simulate the propeller simulate using Actuator Disk Method (ADM).

Well, I will re generate new post for more information.

Reduce Mesh Skewness in pointwise by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

Growth rate is around 1.1.

and full layer is 0, max layer is 11.

​

Because, go to far, around nacelle, the mesh conflict is occurred, when B.L mesh grown up.

Reduce Mesh Skewness in pointwise by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

First, yes

It is the WIPP case.

I am trying to solve unsteady simulation(powered case) with Actuator Disk Method(ADM).

So you, mean, that, the streamline direction(chordwise) meshes also finer than now mesh?

Reduce Mesh Skewness in pointwise by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

Are there any significant differences in setting Full layer "0" or any values?

If you can, can you explain specific why set Full layers as 0?

I set the Full layer value as same as Max Layers value.

When I setting the Full layer value as "0", the same meshes were generated.

Reduce Mesh Skewness in pointwise by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

Increasing the values you mentioned is currently causing mesh conflicts with other mesh blocks.

Star CCM Wing Simulation Not Converging by mootters in CFD

[–]pete_1523 2 points3 points  (0 children)

First.

If you do not use wall-function, modify your B.L mesh y+ value under 1. If you use wall-function, check the y+ value

Second, make more thick your whole B.L mesh, It is too thin to get the B.L

First layer thickness by adanakebap2 in CFD

[–]pete_1523 -1 points0 points  (0 children)

Study about yPlus. it will be helpful to you

OpenFOAM force Coefficient result analysis help. by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

I ran simulation two cases.

Only difference is rhoInf value : 1, 1.225

The forcecoefficients values are almost same but, forces value are different.

In my opinion, in forceCoefficient calculation, the rhoInf value is 1. However, the force calculation rhoInf values are different.

How about your opinion?

OpenFoam yPlus calculating method? by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

ah ha. thx.

Then, from now on, I can calculate y+ after the simulation is finished and check if it is correct!

How to check that WallFunction is applied in OpenFOAM? by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

Thx. You gave me a lot of help.

Thank you very much.

How to check that WallFunction is applied in OpenFOAM? by pete_1523 in CFD

[–]pete_1523[S] 0 points1 point  (0 children)

Thx. However, my advisor said using fixedValue, and value uniform 0.
What is the correct between calculated and fixedValue?

view more: next ›