[inginer]

hello forum,

as the title says my question is the following:

does anybody know a hypersonic cfd FREE code?

best,
Ovidiu

[nakul]

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.

[JLight]

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)

http://www.cfd-online.com/Forums/ope...-aerofoam.html

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.

[chandramurthy]

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/

[inginer]

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

[JLight]

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.

[chandramurthy]

Originally Posted by inginer

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?

[rock.senthilkumar]

Hi JLight,
If u completed updation of AeroFoam for OF 1.6 + , please reply with details.

[ivan_cozza]

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

Originally Posted by inginer

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

[rock.senthilkumar]

Hi Ivan,
Thank you for your suggestion.Surely I will contact them.

[JLight]

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

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

    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

[Solarberiden]

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. :-]

[Andy_bm]

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:

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.

[Solarberiden]

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?

[Andy_bm]

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?

[Solarberiden]

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.
:-]

[Andy_bm]

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.

[Solarberiden]

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. :-]

[nishant_hull]

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