# simpleF, S-A, no convergence, sphere in air at re10^4

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 May 11, 2017, 06:13 simpleF, S-A, no convergence, sphere in air at re10^4 #1 New Member   Anders Utnes Join Date: May 2017 Location: Norway Posts: 6 Rep Power: 2 Sponsored Links Greetings. I'm a student attempting to simulate a few basic geometries and calculate their drag coefficients. The specific case is a 3D grid of 1/4 of a sphere (0.1m diameter), floating in air (300K) thats going past with Re=10^4. I've used the 2D airfoil tutorial as a baseline. simpleFoam, Spalart Allmaras equations. My problem is that after a relatively quick convergence at start, the residuals stops reducing. They fluctuate on the following scales: U: 10^-5 P: 10^-3 NuTilde: 10^-5 And this is ultimately not enought to give me the expected Cd values. Things I've tried in order to solve this, mostly from scanning different forum posts: y+ verified to max 9. Setting U, P, Nutilda tolerance to 1e-12, reltol to 0.05, 0.01, 0.05. Setting simple's nNonOrthogonalCorrectors to 4. Changed nut and nutilda freestream bds and internalstreams to be 1e-4, under the idea that 5*nu (1.57e^-5) would be better than the standard 0.14. Changed grad(U) and grad(nuTilda) shemes to cellLimited leastSquares 1 from gauss linear. Image of case: http://imgur.com/a/oPcWJ Boundary Conditions: (Note that Geo1 & Geo2 are the sphere's wall patches. Left and Bot are symmetryPlane patches. nut: Code: ```dimensions [0 2 -1 0 0 0 0]; internalField uniform 0.0001; boundaryField { Inlet { type freestream; freestreamValue uniform 0.0001; } Outlet { type freestream; freestreamValue uniform 0.0001; } Top { type freestream; freestreamValue uniform 0.0001; } Right { type freestream; freestreamValue uniform 0.0001; } Left { type symmetryPlane; } Bot { type symmetryPlane; } Geo1 { type nutUSpaldingWallFunction; value uniform 0; } Geo2 { type nutUSpaldingWallFunction; value uniform 0; } }``` Nutilda: Code: ```dimensions [0 2 -1 0 0 0 0]; internalField uniform 0.0001; boundaryField { Inlet { type freestream; freestreamValue uniform 0.0001; } Outlet { type freestream; freestreamValue uniform 0.0001; } Top { type freestream; freestreamValue uniform 0.0001; } Right { type freestream; freestreamValue uniform 0.0001; } Left { type symmetryPlane; } Bot { type symmetryPlane; } Geo1 { type fixedValue; value uniform 0; } Geo2 { type fixedValue; value uniform 0; } }``` U: Code: ```dimensions [0 1 -1 0 0 0 0]; internalField uniform (1.57 0 0); boundaryField { Inlet { type freestream; freestreamValue uniform (1.57 0 0); } Outlet { type freestream; freestreamValue uniform (1.57 0 0); } Top { type freestream; freestreamValue uniform (1.57 0 0); } Right { type freestream; freestreamValue uniform (1.57 0 0); } Left { type symmetryPlane; } Bot { type symmetryPlane; } Geo1 { type noSlip; } Geo2 { type noSlip; } }``` P: Code: ```dimensions [0 2 -2 0 0 0 0]; internalField uniform 0; boundaryField { Inlet { type freestreamPressure; } Outlet { type freestreamPressure; } Top { type freestreamPressure; } Right { type freestreamPressure; } Left { type symmetryPlane; } Bot { type symmetryPlane; } Geo1 { type zeroGradient; } Geo2 { type zeroGradient; } }``` Transport properties: Code: ```transportModel Newtonian; rho [1 -3 0 0 0 0 0] 1.18; nu [0 2 -1 0 0 0 0] 1.57e-05;``` Turbulence Properties: Code: ```simulationType RAS; RAS { RASModel SpalartAllmaras; turbulence on; printCoeffs on; }``` ControDict: Code: ```application simpleFoam; startFrom latestTime; startTime 0; stopAt endTime; endTime 5000000; deltaT 1; writeControl timeStep; writeInterval 2000; purgeWrite 0; writeFormat ascii; writePrecision 6; writeCompression off; timeFormat general; timePrecision 6; runTimeModifiable true; functions { forceCoeffs { type forceCoeffs; functionObjectLibs ( "libforces.so" ); outputControl timeStep; timeInterval 1; lRef 0.1; //referanselengde log yes; rho rhoInf; // Indicates incompressible rhoInf 1; // Redundant for incompressible liftDir (0 0 1); dragDir (1 0 0); CofR (0 0 0); // Axle midpoint on ground pitchAxis (0 1 0); magUInf 1.57; patches ( Geo1 Geo2 ); Aref 0.001964; // referanseareal 0.00785 } }``` fvSheme: Code: ```ddtSchemes { default steadyState; } gradSchemes { grad(U) cellLimited leastSquares 1; grad(nuTilda) cellLimited leastSquares 1; default Gauss linear corrected; } divSchemes { default none; div(phi,U) bounded Gauss linearUpwind grad(U); div(phi,nuTilda) bounded Gauss linearUpwind grad(nuTilda); div((nuEff*dev2(T(grad(U))))) Gauss linear; } laplacianSchemes { default Gauss linear corrected; } interpolationSchemes { default linear; } snGradSchemes { default corrected; } wallDist { method meshWave; }``` fvSolution Code: ```solvers { p { solver GAMG; tolerance 1e-12; relTol 0.01; smoother GaussSeidel; } U { solver smoothSolver; smoother GaussSeidel; nSweeps 2; tolerance 1e-12; relTol 0.05; } nuTilda { solver smoothSolver; smoother GaussSeidel; nSweeps 3; tolerance 1e-12; relTol 0.05; } } SIMPLE { nNonOrthogonalCorrectors 4; pRefCell 0; pRefValue 0; residualControl { p 1e-5; U 1e-5; nuTilda 1e-5; } } relaxationFactors { fields { p 0.3; } equations { U 0.7; nuTilda 0.7; } }``` Anyone got any ideas?

 May 18, 2017, 07:37 #2 New Member   Anders Utnes Join Date: May 2017 Location: Norway Posts: 6 Rep Power: 2 UPDATE: I have found a small anamoly in the solution: http://imgur.com/a/oUYJz It appears that there is a problem with the mesh here. I've tried to refine the mesh, but that just gave me 3 such anamolies other places. Anyone got any ideas? I've used gmsh to generate the mesh: Code: ```RefinementLevel=200; ge=0.05; gw=ge/RefinementLevel; l=1.5; h=0.3; d=0.05; //inlet Point(1)={0, 0, 0, 0.5*ge}; Point(2)={0, h, 0, 1.5*ge}; Point(3)={0, 0, h, 1.5*ge}; Point(4)={0, h, h, 2*ge}; //Outlet Point(5)={l, 0, 0, ge}; Point(6)={l, h, 0, 1.5*ge}; Point(7)={l, 0, h, 1.5*ge}; Point(8)={l, h, h, 2*ge}; //Geometry Point(10)={2*l/10, 0, 0, gw}; Point(11)={2*l/10+d, 0, 0, gw}; Point(12)={2*l/10+d, d, 0, gw}; Point(13)={2*l/10+d, 0, d, gw}; Point(14)={2*l/10+2*d, 0, 0, 2*gw}; //Main Lines //Length Line(20)={1, 10}; Line(21)={14, 5}; Line(22)={2, 6}; Line(23)={3, 7}; Line(24)={4, 8}; //inlet Line(25)={1, 3}; Line(26)={3, 4}; Line(27)={4, 2}; Line(28)={2, 1}; //Outlet Line(29)={5, 7}; Line(30)={7, 8}; Line(31)={8, 6}; Line(32)={6, 5}; //Geometry Circle(40)={10, 11, 12}; Circle(41)={10, 11, 13}; Circle(42)={12, 11, 13}; Circle(43)={12, 11, 14}; Circle(44)={13, 11, 14}; //Loops Line Loop(50)={25, 26, 27, 28};//inlet Line Loop(51)={29, 30, 31, 32};//outlet Line Loop(52)={25, 23, -29, -21, -44, -41, -20};//bot Line Loop(53)={-27, 24, 31, -22};//top Line Loop(54)={28, 20, 40, 43, 21, -32, -22};//left Line Loop(55)={-26, 23, 30, -24};//right Line Loop(56)={40, 42, -41};//Geometry 1 Line Loop(57)={42, 44, -43};//Geometry 2 //Planes Plane Surface(60)={50}; Plane Surface(61)={51}; Plane Surface(62)={52}; Plane Surface(63)={53}; Plane Surface(64)={54}; Plane Surface(65)={55}; Ruled Surface(66)={56}; Ruled Surface(67)={57}; //Naming Physical Surface("Inlet")={60}; Physical Surface("Outlet")={61}; Physical Surface("Bot")={62}; Physical Surface("Top")={63}; Physical Surface("Left")={64}; Physical Surface("Right")={65}; Physical Surface("Geo1")={66}; Physical Surface("Geo2")={67}; //Volume Surface Loop(70)={60, 61, 62, 63, 64, 65, 66, 67}; Volume(71)={70}; Physical Volume("Internal")={71};```

 May 18, 2017, 08:11 #3 Senior Member     Uwe Pilz Join Date: Feb 2017 Location: Leipzig, Germany Posts: 263 Rep Power: 4 Without analysing your case en détail: simpleFoam is a steady state solver. You have a Reynolds number of 10,000. In this Re range we get a Kármán vortex street . The iteration round in simple may be seen as pseudo time steps. In your case which is in reality transient it may be that the solver doesn't come to an end in your sense. You may select one or more monitoring point and look when the frequency of changing gets stable. __________________ Uwe Pilz -- Sie ahnen nicht, wieviel Poesie in der Berechnung einer Logarithmentafel enthalten ist (Carl Friedrich Gauß)

 Tags simplefoam convergence, spalart allamras, sphere

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