NACA0012 with rhoCentralFoam
3 Attachment(s)
I am having some problem with a NACA0012 test case using rhoCentralFoam. The freestream mach is 0.75 and there is a shock. I have attached some pictures. There is something wrong with the bcs.
Some of the input options are listed below. Other input files are same as here http://gfoam.svn.sourceforge.net/vie...12_7k_M075_a2/ Hope somebody can point out the mistakes. 0/p Code:
internalField uniform 85418.9; Code:
Code:
Code:
thermoType ePsiThermo<pureMixture<constTransport<specieThermo<eConstThermo<perfectGas>>>>>; 
hi praveen,
Is the solution converges well and where can i really see that you used the rhoCentralFoam for your problem. 
Everything in the above link remains same for rhoCentralFoam except you have to change to
fluxScheme Kurganov; // or Tadmor in system/fvSchemes. The files can be downloaded here http://gfoam.svn.sourceforge.net/vie...5_a2/?view=tar 
NACA0012 with rhoCentralFoam
hi praveen,
I am also trying for different airfoil simulation using rhoCentralFoam using different boundary condition at mach no=0.7. even i am also getting same error wat u r getting on airfoil surface for unstructured grid. But when i solved for structured grid (same airfoil wat i used for unstructured) i am getting perfect solution using rhoCentralFoam for C Grid without any disturbances on airfoil surface. Could you please tell me what s da solution for this type of problem, if u have solved..... Regards NAVEEN.K.M NAL BANGALORE 
I dont know whats the problem. I too got proper result with structured grid for naca case.

NACA0012 with rhoCentralFoam
OK....letś try some other way....can u give me your mail id....
NAVEEN.K.M 
NACA0012 with rhoCentralFoam
hi praveen,
I got the proper results for airfoil using rhoCentralFoam for unstructured grid same as structured grid. Regards NAVEEN 
Hi guys, I encountered the same problem, could you please tell me how do you solve the problems on unstructured grid? Thanks a lot!~


can anybody provide details about preconditioning for the above solver for Mach number approaching zero.
thanks in advance, Regards. 
for the mach number approaching to zero
Quote:
regrads. TCH 
hi
solvers for compressible flows always has Mach number is greater than that of incompressible flows, using preconditioning we can use compressible flow solvers for solving incompressible NS equations ( having Mach Number nearer to zero)
can anybody provide details about the code to implement in openFoam. here I am attaching the link which contains the details about the method. http://openfoamwiki.net/index.php/TestLucaG. thanks in advance regards. 
2 Attachment(s)
Hello all,
I am trying to simulate a NACA 0012 airfoil in transonic flow. I believe that rhoCentralFoam would be the best solver for the compressible & transient simulations. However, I have not used a densitybased solver before and I am struggling with a few issues: 1. What is the best way to check for convergence? When using simpleFoam, I plotted Ux_0 and p_0 residuals. In rhoCentralFoam, there is no p_0 residual (obviously) and the rho_0 residual is 0 from start to finish. 2. Here is what a typical timestep looks like in the log. I find it strange that all of the rho equations have 0 residual and 0 iterations. Any advice? Code:
Mean and max Courant Numbers = 0.00853124 0.92921 Thank you for any suggestions, Dan 
same question for zero density
Hi,
Is there anybody who can help us with this question because many good people have asked it and no one has ever replied properly. Kind Regards, Farshad 

how about kurganovtadmor or AUSM+?
Hi,
I read that and he mentioned that: "The obliqueshock and forwardstep cases run fine but there is some problem with the naca case. The case runs but the solution has strange behaviour near airfoil surface " So i think the airfoil is a problem but why? The other problem is that the kurganovtadmor or any other flux scheme is not available. Kind Regards, Farshad 
naca0012 rhoCentralFoam instabilities
1 Attachment(s)
Hi,
Using Vuorinen's slides on "Compressible RungeKutta 4 LESSolver to OpenFOAM", I implemented RK in rhoCentralFoam. This seems to provide a notable improvement in removing those numerical instabilities. I am still using vanLeer in fvScheme and not gamma. Regards Johan 
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