# forces function VS patchIntegrate

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 June 5, 2010, 16:46 forces function VS patchIntegrate #1 Senior Member   Andrea Pasquali Join Date: Sep 2009 Location: Germany Posts: 142 Rep Power: 7 Hello, I'm tried to calculate the Fx, Fy, Fz on a patch. My run is simpleFoam. With the forces function, during the calculation, for example my Fz was Fz = 13,57 kN (pressure + viscous). At the end of the run, I tried with patchIntegrate and I obtained F = 6,36 kN along a vector (912 778 5540). So Fz is Fz = 6,28 kN. This is strange! There is a 2.16 factor! Am I wronging something? Thank you for any help Andrea __________________ Andrea Pasquali

 June 6, 2010, 10:14 #2 Member   Rickard Hidefjäll Join Date: Jun 2009 Location: Uppsala, Sweden Posts: 39 Rep Power: 8 Maybe I`ve got the same problem. see: 3D simulation with blended wingbody. Lift a 1/3 of what it shuld be. Any wrong? Regards / Rickard

 June 6, 2010, 10:30 #3 Senior Member   Andrea Pasquali Join Date: Sep 2009 Location: Germany Posts: 142 Rep Power: 7 Hi Rickard, I already saw you post! My problem is that I used well forces function to calculate lift and drag coefficients in car analysis; but now with an ulma airplane I'm thinking the value I obtained is too much! Instead with patchIntegrate is too low! Therefore I know the pressure dimension in simpleFoam is p/rho. It could be related to our problem? Do you know if and where I could find a NACA profile to test? Thanks Andrea __________________ Andrea Pasquali

 June 6, 2010, 13:19 #4 Member   Rickard Hidefjäll Join Date: Jun 2009 Location: Uppsala, Sweden Posts: 39 Rep Power: 8 Hi Andrea. "Do you know if and where I could find a NACA profile to test?" The equation for Naca 0009, is; 9/10*(5*(.29690*( (y)^.5)-.12600*y-.35160*((y)^2)+.28430*((y)^3)-.10150*((y)^4) ) ) A good site for wing profile is http://airfoils.worldofkrauss.com/foils for Naca 0009 http://airfoils.worldofkrauss.com/foils/1744 Regards / Rickard

 June 6, 2010, 14:17 #5 Member   Rickard Hidefjäll Join Date: Jun 2009 Location: Uppsala, Sweden Posts: 39 Rep Power: 8 You can use one of my scripts if you like. see permissions in beginning of file Itś at elliptic wing with ability to change angle of attack and twist of wing tip. You could use my wing channel. You had to put the WindChannel34.geo in the same directory as 20100520_2_Exp15.geo http://www.tooslow.net/rattus/CFD_Pi...dChannel34.geo http://www.tooslow.net/rattus/CFD_Pi...20_2_Exp15.geo You open 20100520_2_Exp15.geo in gmsh and do a 2D mesh then you import the saved mesh in enGrid to make a complete OpenFOAM case Good luck Regards / Rickard Last edited by SkunkWorks; June 6, 2010 at 15:29. Reason: wrong adress

 June 10, 2010, 17:21 #6 Member   Rickard Hidefjäll Join Date: Jun 2009 Location: Uppsala, Sweden Posts: 39 Rep Power: 8 Hi see my new post on 3D simulation with blended wingbody. Lift a 1/3 of what it shuld be. Any wrong? I came up with a factor 2,43 Regards Rickard

 April 12, 2011, 10:17 #7 New Member   Join Date: Mar 2011 Posts: 17 Rep Power: 6 I've been having problems with an ahmed body simulation. i ran the case in Komega, Kepsilo, KomegaSST and SpalartAllmaras and in all cases i get a Cd thats somewhere between 2 and 3 times what it should be. Maybe these problems are related..

 April 13, 2011, 20:28 #8 New Member   Alexandre Rubel Join Date: Dec 2010 Location: Launceston, Tasmania AUSTRALIA Posts: 28 Rep Power: 6 I ran simultaion in both steadystate and Transcient simulation for an AUV with the different basic turbulence model. After lots of simulation to find the better scheme i reduce to 200 or 300 % of error for the Cd to 25%. But it's still high. The pressure distribution around the hull seems very good as the other variables. Do you think that the libForces.so library may have errors ?

 August 16, 2011, 03:45 #9 New Member   Caleb Miles Join Date: Jun 2011 Posts: 13 Rep Power: 6 Hello Was anyone able to resolve this issue. I recently posted some other strange force calculation results in another post Strange Results With snappyHexMesh where my force calculations differ by orders of magnitude depending on whether I use a mesh generated by blockMesh or snappyHexMesh. Any insight would be greatly appreciated. Caleb

 August 16, 2011, 11:07 #10 New Member   Join Date: Mar 2011 Posts: 17 Rep Power: 6 I had similar problems but finally fixed them by choosing better div() schemes: {Note: This was for primarily pressure drag, for viscous drag i had a lot of trouble and could never really get a good result} [check this thread, post #6: http://www.cfd-online.com/Forums/ope...fficients.html ] i switched my div(phi,u) scheme from "upwind" to "Gauss linearUpwindV cellMDLimited Gauss linear 1" and it worked. Reduced my drag error from about 120% to 10%. In that thread you can also see the dependency between the result and the mesh quality.

 August 16, 2011, 16:19 #11 New Member   Caleb Miles Join Date: Jun 2011 Posts: 13 Rep Power: 6 Thanks for the quick reply nicolarre, but even after making your suggested change, I had already been using "Gauss linear corrected" for that term, my results are the same. I fear that something much stranger is occuring because as can be seen from the report produced by checkMesh for the mesh produced by snappyHexMesh Code: ```/*---------------------------------------------------------------------------*\ | ========= | | | \\ / F ield | OpenFOAM: The Open Source CFD Toolbox | | \\ / O peration | Version: 1.7.1 | | \\ / A nd | Web: www.OpenFOAM.com | | \\/ M anipulation | | \*---------------------------------------------------------------------------*/ Build : 1.7.x-4bbf33160caf Exec : checkMesh Date : Aug 15 2011 Time : 20:26:19 Host : calebspc PID : 25574 Case : /home/caleb/full_cylinder_flow_snappyHexMesh nProcs : 1 SigFpe : Enabling floating point exception trapping (FOAM_SIGFPE). // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * // Create time Create polyMesh for time = 0 Time = 0 Mesh stats points: 61304 internal points: 0 faces: 119164 internal faces: 59088 cells: 29504 boundary patches: 6 point zones: 0 face zones: 0 cell zones: 0 Overall number of cells of each type: hexahedra: 27888 prisms: 372 wedges: 0 pyramids: 0 tet wedges: 0 tetrahedra: 0 polyhedra: 1244 Checking topology... Boundary definition OK. Point usage OK. Upper triangular ordering OK. Face vertices OK. Number of regions: 1 (OK). Checking patch topology for multiply connected surfaces ... Patch Faces Points Surface topology topAndBottom 80 164 ok (non-closed singly connected) inlet 40 82 ok (non-closed singly connected) outlet 40 82 ok (non-closed singly connected) front 29504 30652 ok (non-closed singly connected) back 29504 30652 ok (non-closed singly connected) circle 908 1816 ok (non-closed singly connected) Checking geometry... Overall domain bounding box (-2 -2 0.1) (2 2 0.15) Mesh (non-empty, non-wedge) directions (1 1 0) Mesh (non-empty) directions (1 1 0) All edges aligned with or perpendicular to non-empty directions. Boundary openness (9.8838e-19 5.74288e-19 -4.82611e-16) OK. Max cell openness = 1.74029e-16 OK. Max aspect ratio = 3.18563 OK. Minumum face area = 2.35607e-06. Maximum face area = 0.00998599. Face area magnitudes OK. Min volume = 1.17804e-07. Max volume = 0.0004993. Total volume = 0.760734. Cell volumes OK. Mesh non-orthogonality Max: 21.7302 average: 4.688 Non-orthogonality check OK. Face pyramids OK. Max skewness = 0.342234 OK. Mesh OK. End``` versus the mesh produced by blockMesh Code: ```/*---------------------------------------------------------------------------*\ | ========= | | | \\ / F ield | OpenFOAM: The Open Source CFD Toolbox | | \\ / O peration | Version: 1.7.1 | | \\ / A nd | Web: www.OpenFOAM.com | | \\/ M anipulation | | \*---------------------------------------------------------------------------*/ Build : 1.7.x-4bbf33160caf Exec : checkMesh Date : Aug 15 2011 Time : 20:26:25 Host : calebspc PID : 25576 Case : /home/caleb/half_cylinder_flow_blockMesh nProcs : 1 SigFpe : Enabling floating point exception trapping (FOAM_SIGFPE). // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * // Create time Create polyMesh for time = 0 Time = 0 Mesh stats points: 4222 internal points: 0 faces: 8110 internal faces: 3890 cells: 2000 boundary patches: 6 point zones: 0 face zones: 0 cell zones: 0 Overall number of cells of each type: hexahedra: 2000 prisms: 0 wedges: 0 pyramids: 0 tet wedges: 0 tetrahedra: 0 polyhedra: 0 Checking topology... Boundary definition OK. Point usage OK. Upper triangular ordering OK. Face vertices OK. Number of regions: 1 (OK). Checking patch topology for multiply connected surfaces ... Patch Faces Points Surface topology down 60 124 ok (non-closed singly connected) right 30 62 ok (non-closed singly connected) up 60 122 ok (non-closed singly connected) left 30 62 ok (non-closed singly connected) cylinder 40 82 ok (non-closed singly connected) defaultFaces 4000 4222 ok (non-closed singly connected) Checking geometry... Overall domain bounding box (-2 0 -0.5) (2 2 0.5) Mesh (non-empty, non-wedge) directions (1 1 0) Mesh (non-empty) directions (1 1 0) All edges aligned with or perpendicular to non-empty directions. Boundary openness (9.98912e-19 1.03887e-16 -1.88857e-18) OK. Max cell openness = 1.942e-16 OK. Max aspect ratio = 1.97696 OK. Minumum face area = 0.00205955. Maximum face area = 0.0785197. Face area magnitudes OK. Min volume = 0.00205955. Max volume = 0.00445575. Total volume = 7.60771. Cell volumes OK. Mesh non-orthogonality Max: 41.2645 average: 10.0965 Non-orthogonality check OK. Face pyramids OK. Max skewness = 0.422837 OK. Mesh OK. End``` The mesh produced by snappyHexMesh seems to be of higher quality in every regard except for a higher aspect ratio and a much smaller minimum cell volume, so I'm really at a loss for what could be going on. I'm not very familiar with snappyHexMesh so I'm not really sure how to reduce the maximum aspect ratio to come in line with blockMesh. If you have any suggestions, however, I would greatly appreciate them. Caleb

 August 17, 2011, 09:19 #12 New Member   Join Date: Mar 2011 Posts: 17 Rep Power: 6 Could you attach/upload the blockMeshDict and the snappyHexMeshDict?

 August 17, 2011, 12:42 #13 New Member   Caleb Miles Join Date: Jun 2011 Posts: 13 Rep Power: 6 Hello nicolarre, Here are the snappyHexMesh case files, the original 3D and the extruded 2D: http://dl.dropbox.com/u/21019547/sna..._circle.tar.gz http://dl.dropbox.com/u/21019547/sna..._circle.tar.gz I just used the half cylinder case from the basic/potential tutorial but the full case I used is here: http://dl.dropbox.com/u/21019547/hal...ockMesh.tar.gz while the full case for the snappyHexMesh is here: http://dl.dropbox.com/u/21019547/ful...HexMesh.tar.gz The snappyHexMeshDict is reproduced below Code: ```/*--------------------------------*- C++ -*----------------------------------*\ | ========= | | | \\ / F ield | OpenFOAM: The Open Source CFD Toolbox | | \\ / O peration | Version: 1.7.1 | | \\ / A nd | Web: www.OpenFOAM.com | | \\/ M anipulation | | \*---------------------------------------------------------------------------*/ FoamFile { version 2.0; format ascii; class dictionary; object snappyHexMeshDict; } // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * // // Which of the steps to run castellatedMesh true; snap true; addLayers true; // Geometry. Definition of all surfaces. All surfaces are of class // searchableSurface. // Surfaces are used // - to specify refinement for any mesh cell intersecting it // - to specify refinement for any mesh cell inside/outside/near // - to 'snap' the mesh boundary to the surface geometry { circle.stl { type triSurfaceMesh; } refinementBox { type searchableBox; min (-1.5 -1.5 -0.1); max ( 1.5 1.5 0.1); } }; // Settings for the castellatedMesh generation. castellatedMeshControls { // Refinement parameters // ~~~~~~~~~~~~~~~~~~~~~ // If local number of cells is >= maxLocalCells on any processor // switches from from refinement followed by balancing // (current method) to (weighted) balancing before refinement. maxLocalCells 1000000; // Overall cell limit (approximately). Refinement will stop immediately // upon reaching this number so a refinement level might not complete. // Note that this is the number of cells before removing the part which // is not 'visible' from the keepPoint. The final number of cells might // actually be a lot less. maxGlobalCells 2000000; // The surface refinement loop might spend lots of iterations refining just a // few cells. This setting will cause refinement to stop if <= minimumRefine // are selected for refinement. Note: it will at least do one iteration // (unless the number of cells to refine is 0) minRefinementCells 100; // Number of buffer layers between different levels. // 1 means normal 2:1 refinement restriction, larger means slower // refinement. nCellsBetweenLevels 6; // Explicit feature edge refinement // ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ // Specifies a level for any cell intersected by its edges. // This is a featureEdgeMesh, read from constant/triSurface for now. features (); // Surface based refinement // ~~~~~~~~~~~~~~~~~~~~~~~~ // Specifies two levels for every surface. The first is the minimum level, // every cell intersecting a surface gets refined up to the minimum level. // The second level is the maximum level. Cells that 'see' multiple // intersections where the intersections make an // angle > resolveFeatureAngle get refined up to the maximum level. refinementSurfaces { circle.stl { // Surface-wise min and max refinement level level (6 6); } } // Resolve sharp angles on fridges resolveFeatureAngle 30; // Region-wise refinement // ~~~~~~~~~~~~~~~~~~~~~~ // Specifies refinement level for cells in relation to a surface. One of // three modes // - distance. 'levels' specifies per distance to the surface the // wanted refinement level. The distances need to be specified in // descending order. // - inside. 'levels' is only one entry and only the level is used. All // cells inside the surface get refined up to the level. The surface // needs to be closed for this to be possible. // - outside. Same but cells outside. refinementRegions { refinementBox { mode inside; levels ((1e15 3)); } } // Mesh selection // ~~~~~~~~~~~~~~ // After refinement patches get added for all refinementSurfaces and // all cells intersecting the surfaces get put into these patches. The // section reachable from the locationInMesh is kept. // NOTE: This point should never be on a face, always inside a cell, even // after refinement. locationInMesh (-1.7 -1.7 0); // Whether any faceZones (as specified in the refinementSurfaces) // are only on the boundary of corresponding cellZones or also allow // free-standing zone faces. Not used if there are no faceZones. allowFreeStandingZoneFaces true; } // Settings for the snapping. snapControls { //- Number of patch smoothing iterations before finding correspondence // to surface nSmoothPatch 3; //- Relative distance for points to be attracted by surface feature point // or edge. True distance is this factor times local // maximum edge length. tolerance 4.0; //- Number of mesh displacement relaxation iterations. nSolveIter 30; //- Maximum number of snapping relaxation iterations. Should stop // before upon reaching a correct mesh. nRelaxIter 5; } // Settings for the layer addition. addLayersControls { // Are the thickness parameters below relative to the undistorted // size of the refined cell outside layer (true) or absolute sizes (false). relativeSizes true; // Per final patch (so not geometry!) the layer information layers { "circle.*" { nSurfaceLayers 4; } } // Expansion factor for layer mesh expansionRatio 1.3; //- Wanted thickness of final added cell layer. If multiple layers // is the // thickness of the layer furthest away from the wall. // Relative to undistorted size of cell outside layer. // is the thickness of the layer furthest away from the wall. // See relativeSizes parameter. finalLayerThickness 0.7; //- Minimum thickness of cell layer. If for any reason layer // cannot be above minThickness do not add layer. // Relative to undistorted size of cell outside layer. // See relativeSizes parameter. minThickness 0.25; //- If points get not extruded do nGrow layers of connected faces that are // also not grown. This helps convergence of the layer addition process // close to features. nGrow 0; // Advanced settings //- When not to extrude surface. 0 is flat surface, 90 is when two faces // make straight angle. featureAngle 60; //- Maximum number of snapping relaxation iterations. Should stop // before upon reaching a correct mesh. nRelaxIter 5; // Number of smoothing iterations of surface normals nSmoothSurfaceNormals 1; // Number of smoothing iterations of interior mesh movement direction nSmoothNormals 3; // Smooth layer thickness over surface patches nSmoothThickness 10; // Stop layer growth on highly warped cells maxFaceThicknessRatio 0.5; // Reduce layer growth where ratio thickness to medial // distance is large maxThicknessToMedialRatio 0.3; // Angle used to pick up medial axis points // Note: changed(corrected) w.r.t 16x! 90 degrees corresponds to 130 in 16x. minMedianAxisAngle 90; // Create buffer region for new layer terminations nBufferCellsNoExtrude 0; // Overall max number of layer addition iterations. The mesher will exit // if it reaches this number of iterations; possibly with an illegal // mesh. nLayerIter 50; } // Generic mesh quality settings. At any undoable phase these determine // where to undo. meshQualityControls { //- Maximum non-orthogonality allowed. Set to 180 to disable. maxNonOrtho 65; //- Max skewness allowed. Set to <0 to disable. maxBoundarySkewness 20; maxInternalSkewness 4; //- Max concaveness allowed. Is angle (in degrees) below which concavity // is allowed. 0 is straight face, <0 would be convex face. // Set to 180 to disable. maxConcave 80; //- Minimum pyramid volume. Is absolute volume of cell pyramid. // Set to a sensible fraction of the smallest cell volume expected. // Set to very negative number (e.g. -1E30) to disable. minVol 1e-13; //- Minimum tet volume. Is absolute volume of the tet formed by the // face-centre decomposition triangle and the cell centre. // Set to a sensible fraction of the smallest cell volume expected. // Set to very negative number (e.g. -1E30) to disable. minTetVol 1e-20; //- Minimum face area. Set to <0 to disable. minArea -1; //- Minimum face twist. Set to <-1 to disable. dot product of face normal //- and face centre triangles normal minTwist 0.05; //- minimum normalised cell determinant //- 1 = hex, <= 0 = folded or flattened illegal cell minDeterminant 0.001; //- minFaceWeight (0 -> 0.5) minFaceWeight 0.05; //- minVolRatio (0 -> 1) minVolRatio 0.01; //must be >0 for Fluent compatibility minTriangleTwist -1; minTetQuality 1e-9; // Advanced //- Number of error distribution iterations nSmoothScale 4; //- amount to scale back displacement at error points errorReduction 0.75; } // Advanced // Flags for optional output // 0 : only write final meshes // 1 : write intermediate meshes // 2 : write volScalarField with cellLevel for postprocessing // 4 : write current intersections as .obj files debug 0; // Merge tolerance. Is fraction of overall bounding box of initial mesh. // Note: the write tolerance needs to be higher than this. mergeTolerance 1E-6; // ************************************************************************* //``` The blockMeshDict for the half-cylinder that was taken from the tutorial cases is below Code: ```/*--------------------------------*- C++ -*----------------------------------*\ | ========= | | | \\ / F ield | OpenFOAM: The Open Source CFD Toolbox | | \\ / O peration | Version: 1.7.1 | | \\ / A nd | Web: www.OpenFOAM.com | | \\/ M anipulation | | \*---------------------------------------------------------------------------*/ FoamFile { version 2.0; format ascii; class dictionary; object blockMeshDict; } // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * // convertToMeters 1; vertices ( (0.5 0 -0.5) (1 0 -0.5) (2 0 -0.5) (2 0.707107 -0.5) (0.707107 0.707107 -0.5) (0.353553 0.353553 -0.5) (2 2 -0.5) (0.707107 2 -0.5) (0 2 -0.5) (0 1 -0.5) (0 0.5 -0.5) (-0.5 0 -0.5) (-1 0 -0.5) (-2 0 -0.5) (-2 0.707107 -0.5) (-0.707107 0.707107 -0.5) (-0.353553 0.353553 -0.5) (-2 2 -0.5) (-0.707107 2 -0.5) (0.5 0 0.5) (1 0 0.5) (2 0 0.5) (2 0.707107 0.5) (0.707107 0.707107 0.5) (0.353553 0.353553 0.5) (2 2 0.5) (0.707107 2 0.5) (0 2 0.5) (0 1 0.5) (0 0.5 0.5) (-0.5 0 0.5) (-1 0 0.5) (-2 0 0.5) (-2 0.707107 0.5) (-0.707107 0.707107 0.5) (-0.353553 0.353553 0.5) (-2 2 0.5) (-0.707107 2 0.5) ); blocks ( hex (5 4 9 10 24 23 28 29) (10 10 1) simpleGrading (1 1 1) hex (0 1 4 5 19 20 23 24) (10 10 1) simpleGrading (1 1 1) hex (1 2 3 4 20 21 22 23) (20 10 1) simpleGrading (1 1 1) hex (4 3 6 7 23 22 25 26) (20 20 1) simpleGrading (1 1 1) hex (9 4 7 8 28 23 26 27) (10 20 1) simpleGrading (1 1 1) hex (15 16 10 9 34 35 29 28) (10 10 1) simpleGrading (1 1 1) hex (12 11 16 15 31 30 35 34) (10 10 1) simpleGrading (1 1 1) hex (13 12 15 14 32 31 34 33) (20 10 1) simpleGrading (1 1 1) hex (14 15 18 17 33 34 37 36) (20 20 1) simpleGrading (1 1 1) hex (15 9 8 18 34 28 27 37) (10 20 1) simpleGrading (1 1 1) ); edges ( arc 0 5 (0.469846 0.17101 -0.5) arc 5 10 (0.17101 0.469846 -0.5) arc 1 4 (0.939693 0.34202 -0.5) arc 4 9 (0.34202 0.939693 -0.5) arc 19 24 (0.469846 0.17101 0.5) arc 24 29 (0.17101 0.469846 0.5) arc 20 23 (0.939693 0.34202 0.5) arc 23 28 (0.34202 0.939693 0.5) arc 11 16 (-0.469846 0.17101 -0.5) arc 16 10 (-0.17101 0.469846 -0.5) arc 12 15 (-0.939693 0.34202 -0.5) arc 15 9 (-0.34202 0.939693 -0.5) arc 30 35 (-0.469846 0.17101 0.5) arc 35 29 (-0.17101 0.469846 0.5) arc 31 34 (-0.939693 0.34202 0.5) arc 34 28 (-0.34202 0.939693 0.5) ); patches ( symmetryPlane down ( (0 1 20 19) (1 2 21 20) (12 11 30 31) (13 12 31 32) ) patch right ( (2 3 22 21) (3 6 25 22) ) symmetryPlane up ( (7 8 27 26) (6 7 26 25) (8 18 37 27) (18 17 36 37) ) patch left ( (14 13 32 33) (17 14 33 36) ) symmetryPlane cylinder ( (10 5 24 29) (5 0 19 24) (16 10 29 35) (11 16 35 30) ) ); mergePatchPairs ( ); // ************************************************************************* //``` Once I install pyFoam I'll make another go at meshing the full cylinder because I had some difficulties with vertex numbering. Thanks so much for your time. Caleb Last edited by calebamiles; August 18, 2011 at 11:39.

 August 18, 2011, 16:41 #14 New Member   Join Date: Mar 2011 Posts: 17 Rep Power: 6 Im' fairly new to openFoam myself, so i may or may not be of much help, Right off the top of my head (because im not at a computer with access to openFoam) you might want to look at the aspect ratio of your blockmesh. If i recall correctly (i think its in the user manual, somewhere) snappyHexMesh dissaproves of blockmeshes with aspect ratio that aren't close to 1. The closer the blockmesh is to aspect ratio 1, the better the snappy mesh result. Speaking of aspect ratio (and taking into account i didn't get the chance to check your case yet) i see you are adding boundary layers to your snappyhexmesh. Those will usually increase your aspect ratio since they are slim. You may also want to look into your case's y+. See if its near your model's requirement. Depending on the type of simulation, viscous friction may or may not be an important factor. For my ahmed's body case, where viscous drag was low compared to preasurre drag i didn't really had much y+ restrictions. On some Airfoil cases i ran however, i had to make sure my y+ was in the right range.

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