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Old   December 8, 2010, 08:17
Default hypersonic cfd free code???
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Ovidiu Michiu
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hello forum,

as the title says my question is the following:

does anybody know a hypersonic cfd FREE code?

best,
Ovidiu
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Old   December 9, 2010, 13:25
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Hi,

At present no solver exists for hypersonic flow in OpenFOAM. But you can always make your own. I was thinking of doing it but just couldn't find time.

If you want you may begin working on it and I could help.
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Old   December 10, 2010, 08:45
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Well...none part of the official package ... there is one called aeroFoam that may be of interest to you

http://www.aero.polimi.it/freecase/?...namic_problems

This post may also be of interest (the above link is taken from here)

New densitybased solver AeroFoam

But I have not tested it (yet!). I am in the process of developing a solver myself. Hypersonic CFD code is a bit too general ... what type of flow conditions are you interested in.
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Old   December 10, 2010, 13:46
Default density based solver
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Hypersonic flows are characterized by strong energy-flow copuling, requiring a coupled solver (density based). Currenly this solver is not avilable in OF. A brief intriduction about this technology is highlighed by Prof. H jasak in the recent opensourcecfd conferece 2010.http://www.opensourcecfd.com/conference2010/proceedings/documents/Session_III/OSCIC2010_Rusche_Jasak.pdf.

alternatively, you can try open source density based code http://www.freecfd.com/
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Old   December 16, 2010, 08:44
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hello JLight,

I have only the Mach number, which is 10 and the vehicle is flying on the layer of the stratosphere of the Earth.

thk for aeroFoam.
I have a small problem. Is not working on OF 1.7.0. My supposition is this version doesn´t have this C++ library: Cloud.H and passiveParticle.H

best,
Ovidiu
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Old   December 16, 2010, 09:51
Default AeroFoam for OpenFOAM-1.7.x
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hi Ovidiu
OpenFoam does have the library. You need to edit the file in the Make directory. I have uploaded the necessary file in Make.zip

That was the easy part , aeroFoam still has many errors . I do not have the time to go through it to figure out the logic and correct the code as of now (assuming i am able too ), but i am open to the possibility in the coming week.

Hopefully you will have better luck than me!

Cheers!

JLight

PS: I also uploaded the log file for building AeroFoam to give you an idea of the problems encountered.
Attached Files
File Type: zip Make.zip (468 Bytes, 45 views)
File Type: txt log.txt (8.8 KB, 50 views)
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Old   December 16, 2010, 10:11
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Quote:
Originally Posted by inginer View Post

I have only the Mach number, which is 10 and the vehicle is flying on the layer of the stratosphere of the Earth.

Ovidiu
U check the order of Knudsen number, is continuum mechanics valid at such a rarefied atmosphere?
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Old   December 25, 2010, 10:56
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Hi JLight,
If u completed updation of AeroFoam for OF 1.6 + , please reply with details.
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Old   December 28, 2010, 06:18
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I suggest you to contact Giulio Romanelli and Elisa Serioli at Politecnico di Milano, the authors of aeroFoam, maybe they could help you. The are very kind guys!

Ivan


Quote:
Originally Posted by inginer View Post
hello JLight,

I have only the Mach number, which is 10 and the vehicle is flying on the layer of the stratosphere of the Earth.

thk for aeroFoam.
I have a small problem. Is not working on OF 1.7.0. My supposition is this version doesn´t have this C++ library: Cloud.H and passiveParticle.H

best,
Ovidiu
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Old   December 28, 2010, 06:43
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Hi Ivan,
Thank you for your suggestion.Surely I will contact them.
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Old   March 19, 2011, 17:42
Default Hypersonic CFD code
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Hi All
Sorry I had gone MIA. I had some personal trouble that are now sorted.

Regarding AeroFoam, I did not get a lot of opportunity to fix it. However, in my attempts I was able to remove all the compiling errors ( to the best I knew was right) by updating the codes.

But I am not sure of a certain section which is the connectivity . In the file "CreateConnectivity.C" @ about line 110

Code:
forAll( mesh.boundaryMesh(), iPatch )
{
    forAll( mesh.boundaryMesh()[iPatch].faceAreas(), ii )
    {
        
        // Input
        id_L = mesh.boundaryMesh()[iPatch].faceCells()[ii];           
        i    = mag(mesh.boundaryMesh()[iPatch].whichFace(id_L));
                 
        // *** ADAPTIVE VERSION *** ( works better with quad/hexa cells )
        if ( adaptiveConnectivitySearch == 1 )
the whichFace() will return -ve indexes from the way it is currently defined. Any ideas why whichFace does that?

More importantly I am not sure what the Authors are trying to do here so I was not sure if it needs 'fixing'.

This however is not reason I get runtime errors! The problem arises in the file "BuldFluxes.C" @ the lines about 57
Code:
    forAll( mesh->Sf(), i )
    {
        // Input 
        
        id_L        = (*mesh).faceOwner()[i];
        id_R        = (*mesh).faceNeighbour()[i];
Not just the above, but all loops that use the mesh->.Sf() . What happens is the loops seems to step over the arrays by 1 all the time (causing an error). I tried working this out but my debugger takes like a hour to step every single time into the code .

Also I would appreciated if someone tried this on a give known working example. I have not done this, may be the results may be different!

Any help will be appreciated.

The files are located here
http://sourceforge.net/projects/aerofoam/

Nishit
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Old   June 17, 2011, 03:42
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JLight, thanks for you major contribution about the correction and update the AeroFoam 1.7.1 version, I tried some cases in the aeroFoam 1.7.1 and I feel that, the code in CreateConeectivity.C line 110 should be changed form

i = mag(mesh.boundaryMesh()[iPatch].whichFace(id_L));

into

i = mag(mesh.boundaryMesh()[iPatch].start() + ii);

during running the case of OneraM6 and YF-17, the storage of connectivity file routing should be changed from

./Data
./Log

to

../Data
../Log

further feedback about this post is welcome. :-]
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Old   January 18, 2012, 09:16
Default AeroFoam 1.7.1
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Hi.
I have downloaded AeroFoam 1.7.1 from http://sourceforge.net/projects/aerofoam/ and has compiled it.Errors at compilation was not found, but when I have begun test AeroFoam on an example OneraM6,ObliqueShock it doesn't work and gives out the following error:
for ObliqueShock log .o file:
Code:
Create time
Create mesh for time = 0
// using new solver syntax:
cellDisplacement
{
solver PCG;
preconditioner DIC;
tolerance 1e-08;
relTol 0;
}
========================================
Reading Thermodynamic Properties...
========================================
gamma [-] = 1.4
Pr [-] = 0.72
R [J/KgK] = 287.05
Cp [J/KgK] = 717.625
Cv [J/KgK] = 1004.67
----------------------------------------
========================================
Reading Initial Conditions...
========================================
Reading field p
Reading field T
Reading field U
This is a start 10 % 
19 % 
This is a start 10 % 
19 % 
29 % 
This is a start 10 % 
19 % 
29 % 
This is a start 10 % 
19 % 
29 % 
This is a start 10 % 
19 % 
29 % 
This is a start 9 % 
19 % 
28 % 
This is a start 9 % 
19 % 
28 % 
----------------------------------------
Creating conservative variables at t^(k)
Creating conservative variables at t^(k-1)
Creating conservative variables at t^(k-2)
Creating conservative variables fluxes at t^(k)
Creating primitive variables gradient fields (optional)
----------------------------------------
========================================
Creating Mesh Connectivity...
========================================
Using adaptive algorithm...
id_LL_i216SIZE84Loop on Internal Faces...
i=0i=1i=2i=3i=4i=5i=6i=7 10 % 
i=8i=9i=10i=11i=12i=13i=14i=15 19 % 
29 % 
39 % 
48 % 
58 % 
67 % 
77 % 
87 % 
96 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
99 % 
38 % 
47 % 
56 % 
66 % 
75 % 
85 % 
94 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
99 % 
i=16i=17i=18i=19i=20i=21i=22i=23 29 % 
i=24i=25i=26i=27i=28i=29i=30i=31 38 % 
i=32i=33i=34i=35i=36i=37i=38i=39 48 % 
i=40i=41i=42i=43i=44i=45i=46i=47 57 % 
i=48i=49i=50i=51i=52i=53i=54i=55 67 % 
i=56i=57i=58i=59i=60i=61i=62i=63 76 % 
i=64i=65i=66i=67i=68i=69i=70i=71 86 % 
i=72i=73i=74i=75i=76i=77i=78i=79 95 % 
i=80i=81i=82i=83----------------------------------------
Loop on Boundary Faces...
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
98 % 
----------------------------------------
========================================
Mesh 
39 % 
48 % 
58 % 
67 % 
77 % 
87 % 
96 % 
9 % 
18 % 
28 % 
37 % 
46 % 
56 % 
65 % 
75 % 
84 % 
94 % 
38 % 
48 % 
57 % 
67 % 
76 % 
86 % 
95 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
98 % 
38 % 
48 % 
57 % 
67 % 
76 % 
86 % 
95 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
98 % 
38 % 
48 % 
57 % 
67 % 
76 % 
86 % 
95 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
98 % 
38 % 
47 % 
56 % 
66 % 
75 % 
85 % 
94 % 
9 % 
19 % 
29 % 
39 % 
49 % 
59 % 
69 % 
79 % 
89 % 
99 % 
========================================
# of Faces = 84
# of Cells = 50
# of BndPatch = 8
0) supersonicInlet @ inlet
1) extrapolatedOutlet @ outlet
2) symmetryPlane @ bottom
3) supersonicInlet @ top
4) empty @ defaultFaces
5) @ procBoundary0to1
6) @ procBoundary0to2
7) @ procBoundary0to3
----------------------------------------
========================================
Numerical Scheme 
========================================
flowType = Euler
timeScheme = RK2
CourantMax = 0
CourantSteps = 25
MonotoneFlux = Roe
HighResFlux = LW
fluxLimiter = VL
entropyFix = HH2
extrapolateBC = 1
residualNorm = L1
minResidual = -1
----------------------------------------
Does everything look fine? [y] to continue [n] otherwise 
Starting time loop...
SIZE84blf fx i=0
blf fx i=1
...........
blf fx i=83
And further the case isn't considered and gives out an error
(Foam::error:rintStack)
For other cases there are same problems.

Thanks.
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Old   January 18, 2012, 09:44
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Actually I have poured a lot of time on aeroFoam for promote more time integration feature for the code but I could not manage to build more feasible and robust flux schemes on high mach number backward facing step (strong expansion wave problems), I am willing to offer my code but I don't know how. And I would like to provoke some others on proceeding the more powerful aerofoam features. Any body interested of sharing my code?
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Old   January 18, 2012, 09:53
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I am interested. what its difference from code Aerofoam, i don't understand? What version openfoam it is constructed? Whether you know how to rectify my error?
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Old   January 18, 2012, 10:06
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On what version the code was constructed didn't matter, I am just using the code on openfoam 2.0 and it is working well. Questions:
1 - What test case are you just running?
2 - Have you ever tried other test cases aerofoam?
3 - you should first locate where is the "blf fx i=1
...........
blf fx i=83" instructions, it looks strange for me and it does not appear to be right for me.
could you please let me know where you locate the "blf fx i = xxx" instructions.
:-]
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Old   January 18, 2012, 10:26
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I tested Aerofoam on obliqueshock case.I don't know how this solver worked,and don't know that means "blf fx i=1" in the log.

I work over a problem stream injection in vacuum. Start Mach numder > 3..4, at present I use rhoCentralFoam on OpenFOAM v2.0.1,heard that aerofoam gives out very good results, and i wanted to compare it.
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Old   January 18, 2012, 11:07
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please leave your email address and I will send you a copy of the code if I've got the time. Currently, I am not on my working post. I guess you need to wait for quite a while. I will get you informed. :-]
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Old   May 31, 2013, 08:49
Default Aerofoam
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Hi Solarbiden,

I would be interested in helping to debug the case. I have previously done some development on openfoam. However I am new to Aerofoam and I was attracted towards it for its applicability in supersonic cases. I was also wondering if it can be used in aeroelastic applications? My email is nishant.nitj@gmail.com for any communication.

Thanks and regards,

Nishant
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