aerofoilNACA0012 tutorial: added speed and angle of attack controls

and force coeffcients calculation

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/0/U

@@ -14,7 +14,27 @@ FoamFile
 }
 // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
 
-Uinlet          (250 0 0);
+speed           250;
+angleOfAttack   0; // degs
+
+angle           #calc "degToRad($angleOfAttack)";
+liftDir         #codeStream
+{
+    codeInclude #{ #include "vector.H" #};
+    code #{ os << vector(-::sin($angle), 0, ::cos($angle)); #};
+};
+
+dragDir         #codeStream
+{
+    codeInclude #{ #include "vector.H" #};
+    code #{ os << vector(::cos($angle), 0, ::sin($angle)); #};
+};
+
+Uinlet         #codeStream
+{
+    codeInclude #{ #include "vector.H" #};
+    code #{ os << $speed*vector(::cos($angle), 0, ::sin($angle)); #};
+};
 
 dimensions      [0 1 -1 0 0 0 0];
 

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/0/k

@@ -14,7 +14,7 @@ FoamFile
 }
 // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
 
-kInlet          0.01;
+kInlet          1e-3;
 
 dimensions      [0 2 -2 0 0 0 0];
 

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/0/omega

@@ -14,7 +14,7 @@ FoamFile
 }
 // * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * //
 
-omegaInlet      10;
+omegaInlet      1;
 
 dimensions      [0 0 -1 0 0 0 0];
 

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/Allclean

@@ -9,6 +9,7 @@ rm -f constant/geometry/NACA0012.obj.gz > /dev/null 2>&1
 
 cleanCase
 
+rm 0/Ma > /dev/null 2>&1
 rm constant/geometry/boundaryLayer.obj > /dev/null 2>&1
 
 #------------------------------------------------------------------------------

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/system/blockMeshDict

@@ -17,22 +17,23 @@ FoamFile
 
 domain
 {
-    xMin -4;
-    xMax  4;
-    zMin -2;
-    zMax  2;
+    xMax  100;
+    zMax  50;
+
+    xMin #neg $xMax;
+    zMin #neg $zMax;
 
     // Number of cells
-    zCells  80; // aerofoil to far field
-    xUCells 30; // upstream
-    xMCells 30; // middle
-    xDCells 40; // downstream
+    zCells  60; // aerofoil to far field
+    xUCells 60; // upstream
+    xMCells 25; // middle
+    xDCells 50; // downstream
 
     // Mesh grading
-    zGrading    40;  // aerofoil to far field
-    xUGrading   5;   // towards centre upstream
-    leadGrading 0.2; // towards leading edge
-    xDGrading   10;  // downstream
+    zGrading    30000;  // aerofoil to far field
+    xUGrading   10;     // towards centre upstream
+    leadGrading 0.005;  // towards leading edge
+    xDGrading   400;    // downstream
 }
 
 aerofoil
@@ -43,8 +44,9 @@ aerofoil
     zTrail  0;
     xUpper  0.3;
     zUpper  0.06;
-    xLower  0.3;
-    zLower -0.06;
+
+    xLower  $xUpper;
+    zLower  #neg $zUpper;
 }
 
 geometry

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/system/controlDict

@@ -22,7 +22,7 @@ startTime       0;
 
 stopAt          endTime;
 
-endTime         1000;
+endTime         2000;
 
 deltaT          1;
 
@@ -34,7 +34,7 @@ purgeWrite      0;
 
 writeFormat     ascii;
 
-writePrecision   8;
+writePrecision   10;
 
 writeCompression off;
 
@@ -48,6 +48,7 @@ functions
 {
     #includeFunc MachNo
     #includeFunc residuals
+    #includeFunc forceCoeffsCompressible
 }
 
 // ************************************************************************* //

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/system/extrudeMeshDict

@@ -21,7 +21,7 @@ sourcePatches (back);
 exposedPatchName front;
 
 extrudeModel  plane;
-thickness     0.1;
+thickness     1;
 
 flipNormals false;
 mergeFaces false;

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/system/forceCoeffsCompressible

@@ -0,0 +1,29 @@
+/*--------------------------------*- C++ -*----------------------------------*\
+  =========                 |
+  \\      /  F ield         | OpenFOAM: The Open Source CFD Toolbox
+   \\    /   O peration     |
+    \\  /    A nd           | Web:      www.OpenFOAM.org
+     \\/     M anipulation  |
+-------------------------------------------------------------------------------
+Description
+    Calculates lift, drag and moment coefficients by summing forces on
+    specified patches for a case where the solver is compressible (pressure is
+    in units M/(LT^2), e.g. Pa).
+
+\*---------------------------------------------------------------------------*/
+
+#include    "$FOAM_CASE/0/U"
+
+patches     (aerofoil);
+
+magUInf     $speed;
+lRef        1;
+Aref        1; // span
+rhoInf      1.2;
+
+CofR        (0.2 0 0);
+pitchAxis   (0 1 0);
+
+#includeEtc "caseDicts/postProcessing/forces/forceCoeffs.cfg"
+
+// ************************************************************************* //

tutorials/compressible/rhoSimpleFoam/aerofoilNACA0012/system/fvSolution

@@ -20,7 +20,7 @@ solvers
     {
         solver          GAMG;
         smoother        GaussSeidel;
-        tolerance       1e-6;
+        tolerance       1e-8;
         relTol          0.01;
     }
 
@@ -28,7 +28,7 @@ solvers
     {
         solver          PBiCGStab;
         preconditioner  DILU;
-        tolerance       1e-6;
+        tolerance       1e-10;
         relTol          0.1;
     }
 }
@@ -37,9 +37,9 @@ SIMPLE
 {
     residualControl
     {
-        p               1e-4;
-        U               1e-4;
-        "(k|omega|e)"   1e-4;
+        p               1e-6;
+        U               1e-5;
+        "(k|omega|e)"   1e-5;
     }
 
     nNonOrthogonalCorrectors 0;
@@ -51,12 +51,12 @@ relaxationFactors
 {
     fields
     {
-        p               0.7;
+        p               0.3;
         rho             0.01;
     }
     equations
     {
-        U               0.3;
+        U               0.7;
         e               0.7;
         "(k|omega)"     0.7;
     }